Airworthiness Directives; Boeing Model 727 Airplanes, 58002-58005 [05-19842]
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58002
Federal Register / Vol. 70, No. 192 / Wednesday, October 5, 2005 / Rules and Regulations
result in cracking of adjacent structure and
consequent reduced structural integrity of the
fuselage.
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.
Inspections and Follow-On/Corrective
Actions
(f) Except as provided by paragraph (g) of
this AD, prior to the accumulation of 15,000
total flight cycles, or within 3,000 flight
cycles after November 1, 2004 (the effective
date of AD 2004–19–06), whichever occurs
later, perform a detailed inspection and eddy
current inspection to detect cracking or
corrosion of the fail-safe straps between the
side fitting of the rear spar bulkhead at BS
955 and the skin, per Figure 2 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 767–53A0100, dated
September 26, 2002.
Note 1: For the purposes of this AD, a
detailed inspection is: ‘‘An intensive
examination of a specific item, installation,
or assembly to detect damage, failure, or
irregularity. Available lighting is normally
supplemented with a direct source of good
lighting at an intensity deemed appropriate.
Inspection aids such as mirror, magnifying
lenses, etc., may be necessary. Surface
cleaning and elaborate procedures may be
required.’’
(1) If no crack or corrosion is found, repeat
the inspections thereafter at intervals not to
exceed 6,000 flight cycles or 36 months,
whichever occurs first.
(2) If any crack or corrosion is found,
before further flight, repair per a method
approved by the Manager, Seattle Aircraft
Certification Office (ACO), FAA; or using a
method approved in accordance with
paragraph (h)(2) of this AD.
(g) For airplanes on which the fail-safe
strap has been replaced before November 1,
2004: Do the actions required by paragraph
(f) of this AD within 12,000 flight cycles after
accomplishing the replacement.
Note 2: Steps 2 and 8 of the Work
Instructions of Boeing Alert Service Bulletin
767–53A0100, dated September 26, 2002,
refer incorrectly to 767 Airplane
Maintenance Manual (AMM) 32–00–20 for
opening the MLG doors; the correct reference
is 767 AMM 32–00–15, which is referred to
in steps 3 and 7 of the Work Instructions.
Step 2 also should state ‘‘Open Main Landing
Gear (MLG) doors’’ instead of ‘‘Open Main
Landing Green (MLG) doors.’’
Alternative Methods of Compliance
(AMOCs)
(h)(1) The Manager, Seattle ACO, FAA, has
the authority to approve AMOCs for this AD,
if requested in accordance with the
procedures found in 14 CFR 39.19.
(2) Before using any AMOC approved in
accordance with 14 CFR 39.19 on any
airplane to which the AMOC applies, notify
the appropriate principal inspector in the
FAA Flight Standards Certificate Holding
District Office.
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(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
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.
Material Incorporated by Reference
(i) You must use Boeing Alert Service
Bulletin 767–53A0100, dated September 26,
2002, to perform the actions that are required
by this AD, unless the AD specifies
otherwise. On November 1, 2004 (69 FR
57636, September 27, 2004), the Director of
the Federal Register approved the
incorporation by reference of this document.
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
https://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 https://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. 05–19939 Filed 10–4–05; 8:45 am]
BILLING CODE 4910–13–P
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
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
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
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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 https://
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
https://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
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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
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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 reidentified subsequent paragraphs
accordingly.
Explanation of Additional Changes
We have simplified paragraph (h)(2)
of the final rule by referring to
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58003
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
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Federal Register / Vol. 70, No. 192 / Wednesday, October 5, 2005 / Rules and Regulations
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.
§ 39.13
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.
2005–20–13 Boeing: Amendment 39–14307.
Docket No. FAA–2005–21085;
Directorate Identifier 2004–NM–252–AD.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by adding the following new
airworthiness directive (AD):
I
Effective Date
(a) This AD becomes effective November 9,
2005.
Corrective Action
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.
Adoption of the Amendment
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.
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
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.
PART 39—AIRWORTHINESS
DIRECTIVES
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
I
1. The authority citation for part 39
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
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.
(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
If the modification specified in paragraph C. of
AD 90–20–14—
Then—
(1) Was done before the effective date of this
AD.
Do the initial HFEC inspection required 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.
Do the modification specified in paragraph C. of AD 90–20–14 at the same 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.
(2) Has not been done before the effective date
of this AD.
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.
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(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.
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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
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Federal Register / Vol. 70, No. 192 / Wednesday, October 5, 2005 / Rules and Regulations
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 § 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
https://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 https://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
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–21138; Directorate
Identifier 2004–NM–131–AD; Amendment
39–14310; AD 2005–20–16]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 737–100, –200, and –200C Series
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
The FAA is adopting a new
airworthiness directive (AD) for certain
Boeing Model 737–100, –200, and
–200C series airplanes. This AD requires
a one-time detailed inspection for
cracking of the lugs of the inboard
SUMMARY:
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58005
attach fittings of the wing leading edge
slat tracks at slat numbers 2 and 5; prior
or concurrent actions for certain
airplanes; repetitive high-frequency
eddy current (HFEC) inspections for
cracking of the lug surfaces of those
inboard attach fittings if necessary; and
replacement of the attach fittings with
new, improved fittings. This AD results
from reports of damage to the lugs of
certain inboard attach fittings of the
leading edge slat tracks. We are issuing
this AD to prevent a lifted slat, which,
if the airplane performs any non-normal
maneuver during takeoff or landing at
very high angles of attack, could lead to
the loss of the slat and reduced control
of the airplane.
DATES: This AD becomes effective
November 9, 2005.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of November 9, 2005.
ADDRESSES: You may examine the AD
docket on the Internet at https://
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:
Nancy Marsh, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton,
Washington 98055–4056; telephone
(425) 917–6440; fax (425) 917–6590.
SUPPLEMENTARY INFORMATION:
the wing leading edge slat tracks at slat
numbers 2 and 5; prior or concurrent
actions for certain airplanes; repetitive
high-frequency eddy current (HFEC)
inspections for cracking of the lug
surfaces of those inboard attach fittings
if necessary; and replacement of the
attach fittings with new, improved
fittings.
Examining the Docket
You may examine the airworthiness
directive (AD) docket on the Internet at
https://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.
We have revised the ‘‘Alternative
Methods of Compliance (AMOCs)’’
paragraph in this AD to clarify the
delegation authority for Authorized
Representatives for the Boeing
Commercial Airplanes Delegation
Option Authorization.
Discussion
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would
apply to certain Boeing Model 737–100,
–200, and –200C series airplanes. That
NPRM was published in the Federal
Register on May 9, 2005 (70 FR 24335).
That NPRM proposed to require a onetime detailed inspection for cracking of
the lugs of the inboard attach fittings of
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Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the comments received.
Support for the NPRM
One commenter, the manufacturer,
concurs with the content of the NPRM.
Request To Disallow Use of Aluminum
Attach Fittings
One commenter requests that we
revise the NPRM to prohibit replacing
aluminum attach fittings with new
aluminum fittings after the effective
date of the AD. The commenter provides
no justification for this request.
We do not agree with this request.
The manufacturer recommends that,
unless cracked, an aluminum attach
fitting need not be replaced until 120
months or 30,000 flight cycles,
whichever comes first, after the effective
date of the AD. We have determined
that the manufacturer recommendation
is sound and that the repetitive
inspections of the aluminum fittings
required by the AD are sufficient to
maintain safety until the aluminum
fittings are removed from service. We
have not changed the AD in this regard.
Explanation of Change Made to This
AD
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.
Conclusion
We have carefully reviewed the
available data, including the comments
that have been submitted, and
determined that air safety and the
public interest require adopting the AD
with the changes described previously.
We have determined that these changes
E:\FR\FM\05OCR1.SGM
05OCR1
]]>Agencies
[Federal Register Volume 70, Number 192 (Wednesday, October 5, 2005)]
[Rules and Regulations]
[Pages 58002-58005]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-19842]
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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 https://
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 https://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
------------------------------------------------------------------------
If the modification specified
in paragraph C. of AD 90-20- Then--
14--
------------------------------------------------------------------------
(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.
------------------------------------------------------------------------
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 https://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 https://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
