[Federal Register: October 5, 2005 (Volume 70, Number 192)]
[Rules and Regulations]
[Page 58002-58005]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr05oc05-6]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-21085; Directorate Identifier 2004-NM-252-AD;
Amendment 39-14307; AD 2005-20-13]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 727 Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for all
Boeing Model 727 airplanes. This AD requires a one-time inspection of
the lower lobe frames of body section 43 to find open holes between
stringers 17L and 17R and to record their location; repetitive high
frequency eddy current (HFEC) inspections for cracks of all open holes;
and related investigative and corrective actions if necessary. This AD
also includes an optional terminating action of installing rivets in
all open tooling holes and all unused lining holes, which would
terminate the repetitive open-hole HFEC inspections once a hole is
plugged with a rivet. This AD results from reports of cracks at open
tooling holes in the lower lobe frames of body section 43. We are
issuing this AD to detect and correct cracks in the frames, which could
result in cracks in the skin panels and rapid decompression of the
airplane.
DATES: This AD becomes effective November 9, 2005.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in the AD as of November 9,
2005.
ADDRESSES: You may examine the AD docket on the Internet at http://dms.dot.gov
or in person at the Docket Management Facility, U.S.
Department of Transportation, 400 Seventh Street SW., Nassif Building,
room PL-401, Washington, DC.
Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle,
Washington 98124-2207, for service information identified in this AD.
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:
Examining the Docket
You may examine the airworthiness directive (AD) docket on the
Internet at http://dms.dot.gov or in person at the Docket Management
Facility office between 9 a.m. and 5 p.m., Monday through Friday,
except Federal holidays. The Docket Management Facility office
(telephone (800) 647-5227) is located on the plaza level of the Nassif
Building at the street address stated in the ADDRESSES section.
Discussion
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to include an AD that would apply to all Boeing Model 727
airplanes. That NPRM was published in the Federal Register on May 2,
2005 (70 FR 22618). That NPRM proposed to require a one-time inspection
of the lower lobe frames of body section 43 to find open holes between
stringers 17L and 17R and to record their location; repetitive high
frequency eddy current (HFEC) inspections for cracks of all open holes;
and related investigative and corrective actions if necessary. That
NPRM also
[[Page 58003]]
proposed to include an optional terminating action of installing rivets
in all open tooling holes and all unused lining holes, which would
terminate repetitive open-hole HFEC inspections once a hole is plugged
with a rivet.
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the comments received.
Request To Clarify the Frequency of the General Visual Inspection
Two commenters request that we clarify the frequency of the general
visual inspection. The commenters point out that the summary of the
NPRM specifies a one-time inspection, but this inspection is not
clearly explained in either the preamble or the body of the NPRM. The
commenters state that the general visual inspection of all body section
43 frames between stringers 17L and 17R is needed only one time to
identify and record all locations of open holes, including liner
attachment holes. If repeat inspections are needed, the record of the
hole locations will indicate exactly where open holes are located.
We agree with the commenters. Both the NPRM and Boeing Alert
Service Bulletin 727-53A0227, dated September 16, 2004 (which was cited
as the applicable source of service information for the actions in the
NPRM), are unclear about the frequency of the general visual
inspection. The compliance table in paragraph 2.E. ``Compliance'' of
the service bulletin states that the general visual inspection is to be
repetitive. Figures 1 through 5 of the service bulletin instruct
operators to record the locations of all open holes and to keep this
information. We understood that, once all the open hole locations were
identified and recorded, repeating the general visual inspection would
not be necessary. This is not clear in the NPRM. Therefore, we have
revised paragraph (g) of the final rule to clarify that the general
visual inspection is a one-time inspection, and the HFEC inspection is
repetitive. We have also clarified the Summary section to reflect this
change. These changes do not increase the scope of the NPRM since these
actions were already specified in the service bulletin and the NPRM
specified to do all inspections in accordance with the service
bulletin.
Request To Remove Requirement To Inspect Certain Open Holes Previously
Modified
The commenter, the airplane manufacturer, requests that we specify
that open holes used for lining attachments (liner attach holes) are
not subject to the repetitive inspection requirements proposed in the
NPRM if the terminating modification of AD 90-20-14, amendment 39-6730
(55 FR 37864, September 14, 1990), was accomplished for that hole. The
commenter states that the proposed actions in the NPRM and the
requirements of AD 90-20-14 conflict. AD 90-20-14 provides for the
installation of a reinforcement angle and strap along the inner flange
of the lower lobe frames in body section 43, which is terminating
action for the repetitive inspections of in-use liner attach holes in
that AD. The commenter states that the NPRM, as written, would require
repeat inspections of all open liner attach holes, regardless of
whether or not these reinforcement angles and straps are installed. The
manufacturer has not received any reports of cracking at in-use liner
attach holes in frames that have the reinforcements installed in
accordance with AD 90-20-14, and the commenter contends that HFEC
repetitive inspections are not necessary if these reinforcements are
installed. The commenter also notes that the HFEC inspections specified
in Boeing Alert Service Bulletin 727-53A0227 are an alternative method
of compliance (AMOC) with the inspections required by paragraph A. of
AD 90-20-14 and are the preferred method of inspection.
We partially agree with the commenter. We agree that it is not
necessary to accomplish the repetitive inspections specified in
paragraph (g) of the NPRM for in-use liner attach holes where the frame
has been reinforced in accordance with AD 90-20-14. We agree with the
commenter's technical justification. We disagree with completely
eliminating all inspections of in-use liner attach holes. Boeing
Service Bulletin 727-53-0068, Revision 4, dated September 14, 1989,
which is cited as the applicable source of service information for the
actions in AD 90-20-14, specifies post-modification inspections of the
in-use liner attach holes with the frame reinforcement modification
installed. We have added a new paragraph (j) and Table 1 to the final
rule to specify that repetitive inspection intervals for in-use liner
attach holes are extended where the frame has been reinforced in
accordance with AD 90-20-14. We have re-identified subsequent
paragraphs accordingly.
Explanation of Additional Changes
We have simplified paragraph (h)(2) of the final rule by referring
to paragraph (k) of the final rule for repair methods.
We have revised the applicability to identify model designations as
published in the most recent type certificate data sheet for the
affected models.
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.
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.
Costs of Compliance
There are about 1,038 airplanes of the affected design in the
worldwide fleet. This AD affects about 616 airplanes of U.S. registry.
The inspection takes between 8 and 15 work hours per airplane per
inspection cycle, depending on the configuration of the airplane. The
average labor rate is $65 per work hour. Based on these figures, the
estimated cost of this AD for U.S. operators is between $320,320 and
$600,600, or between $520 and $975 per airplane, per inspection cycle.
For operators that choose to do the optional terminating action of
installing rivets in all open tooling holes and all unused lining
holes, the actions take between 13 and 23 work hours per airplane,
depending on the configuration of the airplane. The average labor rate
is $65 per work hour. Based on these figures, the estimated cost of the
optional terminating action is between $845 and $1,495 per airplane.
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
[[Page 58004]]
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 Findings
We have determined that this AD will not have federalism
implications under Executive Order 13132. This AD 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.
For the reasons discussed above, I certify that this AD:
(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.
We prepared a regulatory evaluation of the estimated costs to
comply with this AD and placed it in the AD docket. See the ADDRESSES
section for a location to examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the FAA amends 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. The Federal Aviation Administration (FAA) amends Sec. 39.13 by
adding the following new airworthiness directive (AD):
2005-20-13 Boeing: Amendment 39-14307. Docket No. FAA-2005-21085;
Directorate Identifier 2004-NM-252-AD.
Effective Date
(a) This AD becomes effective November 9, 2005.
Affected ADs
(b) Accomplishing the inspections in paragraph (g) of this AD is
an alternative method of compliance (AMOC) for the inspections
required by paragraph A. of AD 90-20-14, amendment 39-6730, if
accomplished in accordance with the requirements of paragraph (k)(2)
of this AD.
Applicability
(c) This AD applies to all Boeing Model 727, 727C, 727-100, 727-
100C, 727-200, and 727-200F series airplanes, certificated in any
category.
Unsafe Condition
(d) This AD was prompted by reports of cracks at open tooling
holes in the lower lobe frames of body section 43. We are issuing
this AD to detect and correct cracks in the frames, which could
result in cracks in the skin panels and rapid decompression of the
airplane.
Compliance
(e) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Service Bulletin Reference
(f) The term ``service bulletin,'' as used in this AD, means the
Accomplishment Instructions of Boeing Alert Service Bulletin 727-
53A0227, dated September 16, 2004.
Inspections
(g) Before the accumulation of 40,000 total flight cycles, or
within 3,500 flight cycles after the effective date of this AD,
whichever occurs later: Do a one-time general visual inspection of
the lower lobe frames to find open holes between stringer 17L and
stringer 17R of body section 43, record their locations, and keep
these records for future reference when accomplishing the actions in
this AD; and do a high-frequency eddy current (HFEC) inspection for
cracks of all open holes, including lining holes. Repeat the HFEC
inspection at intervals not to exceed 3,500 flight cycles until the
optional terminating action in paragraph (i) of this AD is
accomplished. Do all inspections in accordance with the service
bulletin.
Corrective Action
(h) If any crack is found during any inspection required by
paragraph (g) or (j) of this AD: Before further flight, do the
applicable corrective action in paragraph (h)(1) or (h)(2) of this
AD.
(1) If the crack is less than 0.063 inch in length, do the
corrective action and related investigative action in Figure 6 of
the service bulletin.
(2) If the crack is 0.063 inch in length or greater, repair the
crack using a method approved in accordance with paragraph (k) of
this AD. Chapters 51-40-3 and 53-10-4 of the Boeing 727 Structural
Repair Manual (SRM) are approved methods. Except for these SRMs, for
a repair method to be approved, the approval must specifically
reference this AD.
Optional Terminating Action
(i) Installing rivets in all open tooling holes, and all unused
lining holes, according to Part 2 of the Work Instructions of the
service bulletin terminates the repetitive inspection requirements
of paragraph (g) of this AD only for those holes plugged with
rivets. Terminating action for the repetitive inspection
requirements of paragraph (g) of this AD is not permitted for all
lining holes without installed rivets, except as provided by
paragraph (j) of this AD.
Extended Intervals for Repetitive HFEC Inspections
(j) For open holes that are in use for lining installation only:
Doing the applicable actions in Table 1 of this AD extends the
intervals of the repetitive HFEC inspections required by paragraph
(g) of this AD.
Table 1.--Extended Intervals for Repetitive HFEC Inspections
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If the modification specified
in paragraph C. of AD 90-20- Then--
14--
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(1) Was done before the Do the initial HFEC inspection required
effective date of this AD. by paragraph (g) of this AD at the time
specified in that paragraph. Do the
repetitive HFEC inspections required by
paragraph (g) of this AD thereafter at
intervals not to exceed 20,000 flight
cycles.
(2) Has not been done before Do the modification specified in
the effective date of this paragraph C. of AD 90-20-14 at the same
AD. time as the initial HFEC inspection
required by paragraph (g) of this AD,
and repeat the HFEC inspection
thereafter at intervals not to exceed
20,000 flight cycles.
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AMOCs
(k)(1) The Manager, Seattle Aircraft Certification Office (ACO),
has the authority to approve AMOCs for this AD, if requested in
accordance with the procedures found in 14 CFR 39.19.
(2) The inspection methods specified in paragraph (g) of this AD
are AMOCs to the inspection methods required by paragraph A. of AD
90-20-14, amendment 39-6730. Inspection thresholds and repetitive
intervals are not included in or affected by this AMOC. All other
provisions of AD 90-20-14 that are not specifically mentioned above
remain fully applicable and must be met.
(3) An AMOC that provides an acceptable level of safety may be
used for any repair required by this AD, if it is approved by an
[[Page 58005]]
Authorized Representative for the Boeing Commercial Airplanes
Delegation Option Authorization Organization who has been authorized
by the Manager, Seattle ACO, to make those findings. For a repair
method to be approved, the repair must meet the certification basis
of the airplane, and the approval must specifically refer to this
AD.
(4) 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.
Material Incorporated by Reference
(l) You must use Boeing Alert Service Bulletin 727-53A0227,
dated September 16, 2004, to perform the actions that are required
by this AD, unless the AD specifies otherwise. The Director of the
Federal Register approved the incorporation by reference of this
document in accordance with 5 U.S.C. 552(a) and 1 CFR part 51.
Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle,
Washington 98124-2207, for a copy of this service information. You
may review copies at the Docket Management Facility, U.S. Department
of Transportation, 400 Seventh Street SW., room PL-401, Nassif
Building, Washington, DC; on the Internet at http://dms.dot.gov; or
at 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
.
Issued in Renton, Washington, on September 26, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-19842 Filed 10-4-05; 8:45 am]
BILLING CODE 4910-13-P