Airworthiness Directives; Boeing Model 727 Series Airplanes, 55524-55529 [05-18783]
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55524
Federal Register / Vol. 70, No. 183 / Thursday, September 22, 2005 / Rules and Regulations
TABLE 5.—OTHER RELEVANT RULEMAKING—Continued
Applicability
Related Boeing service
bulletin
AD requirement
AD 2000–10–51, amendment
39–11770 (65 FR 37011,
June 13, 2000).
Certain Boeing Model 767 series airplances.
767–54–0074 ..........................
AD 2001–02–07, amendment
39–12091 (66 FR 8085, January 29, 2001).
AD 2001–06–12, amendment
39–12159 (66 FR 17492,
April 2, 2001).
AD 2003–03–02, amendment
39–13026 (68 FR 4374, January 29, 2003).
Certain Boeing Model 767 series airplanes powered by
Pratt & Whitney engines.
Certain Boeing Model 767 series airplanes powered by
General Electric engines.
All Boeing Model 767 series
airplanes.
767–54–0069, 767–54–0080,
and 767–54–0094.
One-time inspection to determine whether
certain bolts are installed in the side load
underwing fittings on both struts, and various follow-on actions, if necessary.
Modification of the nacelle strut and wing
structure. Terminates certain requirements
of AD 94–11–02.
Modification of the nacelle strut and wing
structure. Terminates certain requirements
of AD 94–11–02.
Supersedes AD 94–11–02; Retains all requirements but reduces certain compliance
times for certain inspections, expands the
detailed and eddy current inspections, and
limits the applicability.
AD
Alternative Methods of Compliance (AMOCs)
(q)(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) AMOCs approved previously according
to AD 2004–09–14, amendment 39–13603,
are approved as AMOCs for the
corresponding requirements of this AD.
(3) An AMOC that provides an acceptable
level of safety may be used for any repair
767–54–0069, 767–54–0081,
and 767–54–0094.
767–54A0062 .........................
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, 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
(r) You must use the service information
identified in Table 6 of this AD to perform
the actions that are required by this AD,
unless the AD specifies otherwise.
TABLE 6.—MATERIAL INCORPORATED BY REFERENCE
Revision
level
Service bulletin
Boeing Service Bulletin 767–54A0101 ........................................................................................................
Boeing Service Bulletin 767–54A0101 ........................................................................................................
Boeing Alert Service Bulletin 767–54A0101 ...............................................................................................
(1) The Director of the Federal Register
approved the incorporation by reference of
Boeing Alert Service Bulletin 767–54A0101,
Revision 4, dated February 10, 2005, in
accordance with 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) On June 9, 2004 (69 FR 24947, May 5,
2004), the Director of the Federal Register
approved the incorporation by of Boeing
Service Bulletin 767–54A0101, Revision 3,
dated September 5, 2002.
(3) On May 15, 2001 (66 FR 18523, April
10, 2001), the Director of the Federal Register
approved the incorporation by reference of
Boeing Service Bulletin 767–54A0101,
Revision 1, dated February 3, 2000.
(4) 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.
VerDate Aug<31>2005
16:24 Sep 21, 2005
Jkt 205001
Issued in Renton, Washington, on
September 13, 2005.
Kalene C. Yanamura,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 05–18785 Filed 9–21–05; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2002–NM–66–AD; Amendment
39–14289; AD 2005–19–24]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 727 Series Airplanes
Federal Aviation
Administration, DOT.
ACTION: Final rule.
AGENCY:
SUMMARY: This amendment supersedes
an existing airworthiness directive (AD),
applicable to all Boeing Model 727
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Date
1
3
4
February 3, 2000.
September 5, 2002.
February 10, 2005.
series airplanes, that currently requires
repetitive pre-modification inspections
to detect cracks in the forward support
fitting of the number 1 and number 3
engines; and repair, if necessary. That
AD also provides for an optional high
frequency eddy current inspection, and,
if possible, modification of the fastener
holes; and various follow-on actions;
which would terminate the repetitive
pre-modification inspections. This
amendment expands the area to be
inspected; requires accomplishment of
the previously optional (and
subsequently revised) modification,
which terminates certain repetitive
inspections; and adds repetitive postmodification inspections to detect
cracking of the fastener holes, and
corrective actions if necessary. The
actions specified by this AD are
intended to prevent fatigue cracking of
the forward support fitting of the
number 1 and number 3 engines, which
could result in failure of the support
fitting and consequent separation of the
engine from the airplane. This action is
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Federal Register / Vol. 70, No. 183 / Thursday, September 22, 2005 / Rules and Regulations
intended to address the identified
unsafe condition.
DATES: Effective October 27, 2005.
The incorporation by reference of
Boeing Service Bulletin 727–54A0010,
Revision 6, including Appendix A,
dated August 23, 2001, as listed in the
regulations, is approved by the Director
of the Federal Register as of October 27,
2005.
The incorporation by reference of
Boeing Service Bulletin 727–54A0010,
Revision 4, dated January 30, 1997, as
listed in the regulations, was approved
previously by the Director of the Federal
Register as of March 18, 1997 (62 FR
9359, March 3, 1997).
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)
by superseding AD 97–05–08,
amendment 39–9952 (62 FR 9359,
March 3, 1997), which is applicable to
all Boeing Model 727 series airplanes,
was published in the Federal Register
on May 1, 2003 (68 FR 23231). The
action proposed to continue to require
repetitive pre-modification inspections
to detect cracks in the forward support
fitting of the number 1 and number 3
engines, and repair if necessary. The
action also proposed to expand the area
to be inspected; require accomplishment
of the previously optional (and
subsequently revised) modification,
which would terminate certain
repetitive inspections; and add
repetitive post-modification inspections
to detect cracking of the fastener holes,
and corrective actions if necessary.
Comments
Interested persons have been afforded
an opportunity to participate in the
making of this amendment. Due
consideration has been given to the
comments received.
Requests To Revise the Applicability
One commenter requests that the
applicability of the proposed AD be
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15:53 Sep 21, 2005
Jkt 205001
revised to apply only to Boeing Model
727 airplanes equipped with fittings
having part number (P/N) 65–18722–xx.
The commenter states that its Model
727–100 fleet does not include any
airplanes equipped with fittings having
that P/N. Because it changed the
affected fittings during a re-engine
modification in accordance with
Supplemental Type Certificate (STC)
SA8472SW, it was granted an alternate
method of compliance (AMOC) for AD
97–05–08. The commenter asserts that
revising the proposed applicability will
prevent operators that do not have the
affected fittings installed from having to
request an AMOC for the requirements
of the proposed AD.
Another commenter requests that a
statement be added to the proposed AD
to exempt airplanes modified in
accordance with STC SA4363NM. The
commenter asserts that inclusion of this
statement will make it perfectly clear to
operators whether or not they are in
compliance with the AD.
We acknowledge the commenters’
concern and, as we state in paragraph
(t)(2) of this AD, AMOCs previously
approved according to AD 97–05–08 are
acceptable for compliance with the
corresponding requirements of this AD.
These AMOCs address the commenter’s
concern. We find that no further
clarifications are necessary and have
made no change to the final rule in this
regard.
Request To Add Language Specific to
Airplanes With ‘‘Hush Kit’’ STCs
Installed
A third commenter requests that
specific language be included in the
final rule stating that airplanes modified
in accordance with STCs SA3993NM,
SA4833NM, SA5839NM, and
ST00350AT may be inspected and
modified in accordance with Boeing
Service Bulletin 727–54A0010, Revision
6, without change. (Boeing Service
Bulletin 727–54A0010, Revision 6,
dated August 23, 2001, was referenced
in the proposed AD as the appropriate
source of service information for
accomplishing the new actions). These
STCs install noise suppression
modification equipment (hush kits) on
Model 727 airplanes. The commenter
states that including this information in
the AD, in lieu of making operators
request AMOCs, will avoid confusion
among operators with airplanes
equipped with these STCs. The
commenter submitted substantiating
data to support its request.
We do not agree. The static strength
data analysis of the affected structure
submitted was not sufficient to show
that the commenter’s request would
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55525
result in an acceptable level of safety.
Damage tolerance assessment is needed
to determine if the inspections and
modifications described in Boeing
Service Bulletin 727–54A0010, Revision
6, are appropriate for airplanes modified
in accordance with these STCs. In this
case, the ability to inspect the affected
area and changes in fatigue stress levels
need to be addressed. Additionally, the
inspections and modifications specified
in the service bulletin specifically
address only affected original
equipment manufacturer configurations.
However, as we explained previously,
we will consider requests for AMOCs
submitted with sufficient technical
justification to support the request. We
have made no change to the final rule
regarding this issue.
Request To Change the Method of
Inspection
Another commenter, the
manufacturer, requests that we revise
paragraphs (d)(1) and (d)(3) of the
proposed AD to revise the method of
inspection. Specifically, the commenter
recommends revising ‘‘* * * If any
corrosion is found, before further flight,
remove the corrosion in accordance
with Figure 5 of the service bulletin,
and perform a general visual inspection
to detect cracking * * *’’ to read
‘‘* * * If any corrosion is found, before
further flight, remove the corrosion in
accordance with Figure 5 of the service
bulletin, and perform a HFEC inspection
to detect cracking * * *.’’ The
commenter asserts that the high
frequency eddy current (HFEC)
inspection is a better method than a
surveillance inspection and will provide
an adequate level of safety by enabling
operators to find small cracks.
We partially agree with the
commenter. We find that an HFEC
inspection should be accomplished after
removal of corrosion. However, we do
not agree that it is necessary to revise
paragraphs (d)(1) and (d)(3) of this final
rule as requested. Paragraphs (d)(1) and
(d)(3) require any corrosion found to be
removed in accordance with Figure 5 of
Boeing Service Bulletin 727–54A0010,
Revision 6, dated August 23, 2001. Step
5 of Figure 5 of the service bulletin
includes procedures for doing an HFEC
inspection for cracks and repairing any
cracks found once the corrosion has
been identified and removed from the
affected area. The general visual
inspection required by paragraphs (d)(1)
and (d)(3) follows the instructions given
in Figure 1, Step 2, of the service
bulletin. We find that no change to the
final rule is necessary regarding this
issue.
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Federal Register / Vol. 70, No. 183 / Thursday, September 22, 2005 / Rules and Regulations
Request To Refer Specifically to PostModification Inspections
The same commenter also requests
that paragraph (m) of the proposed AD
be revised to refer to the postmodification inspections in Revision 5
of Boeing Alert Service Bulletin 727–
54A0010, dated February 15, 2001.
Specifically, the commenter
recommends revising ‘‘* * *
Inspections done before the effective
date of this AD in accordance with
Boeing Alert Service Bulletin 727–
54A0010, Revision 5, dated February 15,
2001, are acceptable for compliance
with the corresponding inspection
requirements of this paragraph * * *.’’
to ‘‘* * * Inspections done before the
effective date of this AD in accordance
with Part III of the Accomplishment
Instructions of Boeing Alert Service
Bulletin 727–54A0010, Revision 5,
dated February 15, 2001, are acceptable
for compliance with the corresponding
inspection requirements of this
paragraph * * *.’’ The commenter
believes that, for airplanes that have
accomplished the modification, only the
repeat post-modification inspection
requirements of Revision 5 of the
service bulletin provide an equivalent
level of safety for the fleet.
We agree with the request for the
reason provided by the commenter. It
was our intent to refer specifically to
Part III of the Accomplishment
Instructions of Revision 5 of the service
bulletin in paragraph (m). Therefore, we
have revised paragraph (m) of this final
rule to specifically refer to Part III of the
Accomplishment Instructions of
Revision 5 of the service bulletin for
accomplishment of post-modification
inspections done before the effective
date of the AD.
Explanation of Additional Changes to
the Proposed AD
Boeing has received a Delegation
Option Authorization (DOA). We have
revised this final rule to delegate the
authority to approve an alternative
method of compliance for any repair
required by this AD to the Authorized
Representative for the Boeing DOA
Organization rather than the Designated
Engineering Representative (DER).
Accordingly, we have added paragraph
(t)(3) to this final rule and revised the
wording of paragraphs (h)(1) and (i) of
this AD. We have also revised the
wording of paragraph (t)(1) of this final
rule (specified as paragraph (s)(1) in the
proposed AD) for reasons discussed
under ‘‘Changes to 14 CFR part 39/Effect
on the AD.’’
Because the language in Note 6 of the
proposed AD is regulatory in nature,
that note has been redesignated as
paragraph (r) of this final rule. We have
re-identified subsequent notes and
paragraphs accordingly.
Conclusion
After careful review of the available
data, including the comments noted
above, the FAA has determined that air
safety and the public interest require the
adoption of the rule with the changes
previously described. The FAA has
determined that these changes will
neither increase the economic burden
on any operator nor increase the scope
of the AD.
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.
AD 97–05–08 inspections, per inspection
cycle.
Inspections before structural rework, per
inspection cycle.
Structural rework .......................................
Inspections after structural rework, per inspection cycle.
15:53 Sep 21, 2005
Jkt 205001
Cost of
parts
Change to Labor Rate Estimate and
Airplane Fleet Data
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.
We have also revised the cost impact
information to more accurately describe
the number of airplanes of the affected
design in the current worldwide and
U.S. fleets.
Cost Impact
There are approximately 1,009
airplanes of the affected design in the
worldwide fleet. The FAA estimates that
587 airplanes of U.S. registry will be
affected by this AD.
We provide the following cost
estimates for this AD:
Cost per
airplane
Cost for the U.S. fleet
2
$65
$0
$130
$76,310, per inspection cycle.
14
65
0
910
534,170, per inspection cycle.
7
12
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
VerDate Aug<31>2005
Average
labor rate
per hour
Work
hours
Action
The regulation now includes material
that relates to altered products, special
flight permits, and AMOCs. Because we
have now included this material in part
39, only the office authorized to approve
AMOCs is identified in each individual
AD. However, for clarity and
consistency in this final rule, we have
retained the language of the NPRM
regarding that material, except for the
revisions to certain language discussed
previously.
65
65
7,875
0
8,330
780
4,889,710.
457,860, per inspection cycle.
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
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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
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Federal Register / Vol. 70, No. 183 / Thursday, September 22, 2005 / Rules and Regulations
‘‘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
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:
I
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. Section 39.13 is amended by
removing amendment 39–9952 (62 FR
9359, March 3, 1997), and by adding a
new airworthiness directive (AD),
amendment 39–14289, to read as
follows:
I
2005–19–24 Boeing: Amendment 39–14289.
Docket 2002–NM–66–AD. Supersedes
AD 97–05–08, Amendment 39–9952.
Applicability: All Model 727 series
airplanes, certificated in any category.
Note 1: This AD applies to each airplane
identified in the preceding applicability
provision, regardless of whether it has been
modified, altered, or repaired in the area
subject to the requirements of this AD. For
airplanes that have been modified, altered, or
repaired so that the performance of the
requirements of this AD is affected, the
owner/operator must request approval for an
alternative method of compliance in
accordance with paragraph (t)(1) of this AD.
The request should include an assessment of
the effect of the modification, alteration, or
repair on the unsafe condition addressed by
this AD; and, if the unsafe condition has not
been eliminated, the request should include
specific proposed actions to address it.
Compliance: Required as indicated, unless
accomplished previously.
To prevent fatigue cracking of the forward
support fitting of the number 1 and number
3 engines, which could result in failure of the
support fitting and consequent separation of
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Jkt 205001
the engine from the airplane, accomplish the
following:
Restatement of Requirements of AD 97–05–
08
Inspections
(a) Within 100 days or 600 flight cycles
after March 18, 1997 (the effective date of AD
97–05–08, amendment 39–9952), whichever
occurs first, accomplish paragraphs (a)(1),
(a)(2), and (a)(3) of this AD, in accordance
with Boeing Service Bulletin 727–54A0010,
Revision 4, dated January 30, 1997.
(1) Perform a visual inspection to detect
cracks of the upper and lower flanges, and
the vertical web of the forward support fitting
of the number 1 and number 3 engines, in
accordance with Part 1—Pre-Modification
Inspections of the Accomplishment
Instructions of the service bulletin.
(2) Perform a high frequency eddy current
(HFEC) inspection to detect cracks of the
forward flange of the support fitting adjacent
to the collars of two fasteners of the number
1 and number 3 engines, in accordance with
Part 1—Pre-Modification Inspections of the
Accomplishment Instructions of the service
bulletin.
(3) Perform a detailed inspection to detect
cracks of the upper and lower flanges
adjacent to six fasteners of the fitting of the
number 1 and number 3 engines, in
accordance with Part 1—Pre-Modification
Inspections of the Accomplishment
Instructions of the service bulletin.
Note 2: 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.’’
(b) If no crack is detected during the
inspections required by paragraph (a) of this
AD, repeat those inspections thereafter at
intervals not to exceed 100 days or 600 flight
cycles, whichever occurs first, until the
initial inspections required by paragraph (d)
of this AD have been accomplished.
(c) If any crack is detected during any
inspection required by paragraph (a) of this
AD, prior to further flight, repair the forward
support fitting in accordance with a method
approved by the Manager, Seattle Aircraft
Certification Office (ACO), FAA.
New Requirements of This AD
Note 3: Where there are differences
between the service bulletin and this AD, this
AD prevails.
Inspections: All Airplanes
(d) For all airplanes: Within 600 flight
cycles or 100 days after the effective date of
this AD, whichever occurs first, inspect the
forward support fitting of the number 1 and
number 3 engines, as specified in paragraphs
(d)(1), (d)(2), (d)(3), (d)(4), and (d)(5) of this
AD, in accordance with Part I of the
Accomplishment Instructions of Boeing
Service Bulletin 727–54A0010, Revision 6,
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55527
dated August 23, 2001. Accomplishment of
these initial inspections terminates the
inspection requirements of paragraphs (a)
and (b) of this AD.
(1) Perform a general visual inspection to
detect corrosion and cracking of the fittings
in areas inboard of the side of the body, in
accordance with Figure 1 of the service
bulletin. If any corrosion is found, before
further flight, remove the corrosion by
accomplishing all of the actions in and in
accordance with Figure 5 of the service
bulletin, and then perform a general visual
inspection to detect cracking of the area, in
accordance with the service bulletin.
Note 4: For the purposes of this AD, a
general visual inspection is: ‘‘A visual
examination of an interior or exterior area,
installation, or assembly to detect obvious
damage, failure, or irregularity. This level of
inspection is made from within touching
distance unless otherwise specified. A mirror
may be necessary to ensure visual access to
all surfaces in the inspection area. This level
of inspection is made under normally
available lighting conditions such as
daylight, hangar lighting, flashlight, or
droplight and may require removal or
opening of access panels or doors. Stands,
ladders, or platforms may be required to gain
proximity to the area being checked.’’
(2) Perform an HFEC inspection to detect
cracking of the upper and lower horizontal
flanges and post tangs of the fittings from
inside the airplane, in accordance with
Figure 1 of the service bulletin.
(3) Perform a general visual inspection to
detect cracking and corrosion of the fittings
in areas outboard of the side of the body, in
accordance with Figure 1 of the service
bulletin. If any corrosion is found, before
further flight, remove the corrosion by
accomplishing all of the actions in and in
accordance with Figure 5 of the service
bulletin, and perform a general visual
inspection to detect cracking of the area, in
accordance with the service bulletin.
(4) Perform a detailed inspection to detect
cracking and corrosion of the web in areas
outboard of the side of the body, in
accordance with Figure 1 of the service
bulletin. If any corrosion is found, before
further flight, remove the corrosion in
accordance with Figure 5 of the service
bulletin, and perform thickness
measurements and detailed and HFEC
inspections of the vertical web inboard and
outboard of the side of the body to detect
corrosion and cracking, in accordance with
Figure 2 of the service bulletin. If the web
thickness is less than 0.130 inch, do
paragraph (i) of this AD.
(5) Perform detailed and HFEC inspections
to detect cracking of the upper and lower
horizontal flanges at the side of the body, in
accordance with Figure 1 of the service
bulletin.
Additional Inspections: Group 2 Airplanes
(e) For Group 2 airplanes, as identified in
Boeing Service Bulletin 727–54A0010,
Revision 6, dated August 23, 2001: Within
600 flight cycles or 100 days after the
effective date of this AD, whichever occurs
first, inspect the forward support fitting of
the number 1 and number 3 engines at the
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Federal Register / Vol. 70, No. 183 / Thursday, September 22, 2005 / Rules and Regulations
firewall to detect cracking, as specified in
paragraphs (e)(1), (e)(2), (e)(3), and (e)(4) of
this AD, in accordance with Part I of the
Accomplishment Instructions of the service
bulletin.
(1) Perform a detailed inspection to detect
cracking of the aft side of the upper
horizontal flange, in accordance with Figure
1 of the service bulletin.
(2) Perform a low frequency eddy current
(LFEC) or an open hole HFEC inspection to
detect cracking of the aft side of the upper
horizontal flange, in accordance with Figure
1 of the service bulletin.
(3) Perform a detailed inspection to detect
cracking of the aft side of the lower
horizontal flange, in accordance with Figure
1 of the service bulletin.
(4) Perform an HFEC inspection to detect
cracking of the aft side of the lower
horizontal flange, in accordance with Figure
1 of the service bulletin.
approval must specifically refer to this AD;
or
(2) Do the modification specified in
paragraph (j) of this AD.
No Cracking Found: Follow-on Inspections,
All Airplanes
(f) For all airplanes: If no cracking is found
during any inspection required by paragraph
(d) of this AD, repeat the applicable
inspections within the applicable intervals
specified in paragraph 1.E., Table 1, of
Boeing Service Bulletin 727–54A0010,
Revision 6, dated August 23, 2001, until the
modification required by paragraph (j) of this
AD has been done.
No Cracking Found: Additional Follow-on
Inspections, Group 2 Airplanes
(g) For Group 2 airplanes only: If no
cracking is found during the inspections
required by paragraph (e) of this AD, repeat
the inspections on the upper and lower
outboard flange at the firewall within the
applicable intervals specified in paragraph
1.E., Table 1, of Boeing Service Bulletin 727–
54A0010, Revision 6, dated August 23, 2001.
(1) Repeat the inspections of the upper
outboard flange at the firewall until the
modification required by paragraph (j) of this
AD has been done.
(2) Repeat the inspections of the lower
outboard flange at the firewall indefinitely.
There is no terminating action for the
inspections of this area.
Note 5: Boeing Service Bulletin 727–
54A0010, Revision 6, dated August 23, 2001,
does not provide instructions for modifying
the fastener holes of the lower outboard
flange at the firewall.
Modification
(j) Except as required by paragraphs (h), (i),
and (q) of this AD: Within 3,000 flight cycles
or 24 months after the effective date of this
AD, whichever occurs first, modify the
fastener holes, in accordance with Part II of
the Accomplishment Instructions of Boeing
Service Bulletin 727–54A0010, Revision 6,
dated August 23, 2001. Accomplishment of
the modification terminates the repetitive
inspections required by paragraphs (f) and
(g)(1) of this AD.
Modification in Accordance With Prior
Service Bulletin Revision
(k) For airplanes modified before the
effective date of this AD in accordance with
Boeing Service Bulletin 727–54A0010,
Revision 4, dated January 30, 1997:
Paragraph (j) of this AD requires
accomplishment of additional procedures in
accordance with Revision 6 of the service
bulletin. To the extent that certain
modification procedures were performed in
accordance with Revision 4, those actions do
not need to be repeated when performing the
modification required in paragraph (j) of this
AD.
(l) A modification done before the effective
date of this AD in accordance with Boeing
Alert Service Bulletin 727–54A0010,
Revision 5, dated February 15, 2001, is
acceptable for compliance with the
requirements of paragraph (j) of this AD.
Cracking Found: Any Airplane
(h) For any airplane: If any crack is found
during any inspection required by paragraph
(d), (e), (f), or (g) of this AD, before further
flight, do the actions specified in either
paragraph (h)(1) or (h)(2) of this AD.
(1) Replace or repair the fitting in
accordance with a method approved by the
Manager, Seattle ACO; or according to data
meeting the certification basis of the airplane
approved by an Authorized Representative
for the Boeing Delegation Option
Authorization (DOA) 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
VerDate Aug<31>2005
15:53 Sep 21, 2005
Jkt 205001
Web Thickness Less Than 0.130 Inch: Any
Airplane
(i) For any airplane: If the web thickness
measured during accomplishment of
paragraph (d)(4) of this AD is less than 0.130
inch, before further flight, replace or repair
the fitting in accordance with a method
approved by the Manager, Seattle ACO; or
according to data meeting the certification
basis of the airplane approved by an
Authorized Representative for the Boeing
DOA 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.
Post-Modification Inspections
(m) Inspect as specified in paragraphs
(m)(1), (m)(2), and (n) of this AD, as
applicable, to detect cracking and corrosion,
in accordance with Part III of the
Accomplishment Instructions of Boeing
Service Bulletin 727–54A0010, Revision 6,
dated August 23, 2001. Inspections done
before the effective date of this AD in
accordance with Part III of Boeing Alert
Service Bulletin 727–54A0010, Revision 5,
dated February 15, 2001, are acceptable for
compliance with the corresponding
inspection requirements of this paragraph.
(1) For all airplanes: Do an open hole HFEC
inspection of the fastener holes in the
forward support fitting of the number 1 and
number 3 engines, at the locations shown in
Figure 4 of the service bulletin.
PO 00000
Frm 00016
Fmt 4700
Sfmt 4700
(2) For Group 2 airplanes: Do an open hole
HFEC inspection of the fastener holes in the
forward support fitting of the number 1 and
number 3 engines, at the locations shown in
Figure 4 of the service bulletin.
(n) Perform the inspections specified in
paragraph (m) of this AD at the later of the
times specified in paragraphs (n)(1) and
(n)(2) of this AD.
(1) Within 3,000 flight cycles or 24 months,
whichever occurs first, after accomplishment
of the modification required by paragraph (j)
of this AD.
(2) Within 600 flight cycles or 100 days,
whichever occurs first, after the effective date
of this AD.
Follow-On/Corrective Actions
(o) If no cracking is found during any
inspection required by paragraph (m) of this
AD: Repeat the inspections specified in
paragraph (m) of this AD thereafter within
the applicable intervals specified in
paragraph 1.E., Table 1, of Boeing Service
Bulletin 727–54A0010, Revision 6, dated
August 23, 2001. Accomplishment of the
modification specified in paragraph (j) of this
AD does not terminate the requirement to
repetitively perform the post-modification
inspections specified in Part III of the service
bulletin.
(p) If any cracking is detected during any
inspection required by paragraph (m) of this
AD: Before further flight, repair in
accordance with Boeing Service Bulletin
727–54A0010, Revision 6, dated August 23,
2001; except as required by paragraph (q) of
this AD.
Exception to Corrective Actions
(q) Where Boeing Service Bulletin 727–
54A0010, Revision 6, dated August 23, 2001,
specifies to contact Boeing for appropriate
action: Before further flight, replace or repair
the fitting in accordance with a method
approved by the Manager, Seattle ACO; or
according to data meeting the certification
basis of the airplane approved by an
Authorized Representative for the Boeing
DOA 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.
Reporting Not Required
(r) Boeing Service Bulletin 727–54A0010,
Revision 6, dated August 23, 2001,
recommends that operators report inspection
results to the manufacturer; however, this AD
does not contain this requirement.
Parts Installation
(s) As of the effective date of this AD, no
person may install a forward support fitting
on any airplane, unless it has been inspected
and modified, as applicable, in accordance
with the requirements of this AD.
Alternative Methods of Compliance
(t)(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) AMOCs previously approved according
to AD 97–05–08 are acceptable for
E:\FR\FM\22SER1.SGM
22SER1
Federal Register / Vol. 70, No. 183 / Thursday, September 22, 2005 / Rules and Regulations
compliance with the corresponding
requirements of this AD.
(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
DOA 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.
Note 6: Information concerning the
existence of approved alternative methods of
compliance with this AD, if any, may be
obtained from the Seattle ACO.
DEPARTMENT OF TRANSPORTATION
Special Flight Permits
(u) Special flight permits may be issued
according to sections 21.197 and 21.199 of
the Federal Aviation Regulations (14 CFR
21.197 and 21.199) to operate the airplane to
a location where the requirements of this AD
can be accomplished.
AGENCY:
Incorporation by Reference
(v) Unless otherwise specified in this AD,
the actions must be done in accordance with
Boeing Service Bulletin 727–54A0010,
Revision 4, dated January 30, 1997; and
Boeing Service Bulletin 727–54A0010,
Revision 6, including Appendix A, dated
August 23, 2001; as applicable.
(1) The incorporation by reference of
Boeing Service Bulletin 727–54A0010,
Revision 6, including Appendix A, dated
August 23, 2001, is approved by the Director
of the Federal Register in accordance with 5
U.S.C. 552(a) and 1 CFR part 51.
(2) The incorporation by reference of
Boeing Service Bulletin 727–54A0010,
Revision 4, dated January 30, 1997, was
approved previously by the Director of the
Federal Register as of March 18, 1997 (62 FR
9359, March 3, 1997).
(3) 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 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.
Effective Date
(w) This amendment becomes effective on
October 27, 2005.
Issued in Renton, Washington, on
September 8, 2005.
Kalene C. Yanamura,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 05–18783 Filed 9–21–05; 8:45 am]
BILLING CODE 4910–13–P
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–22486; Directorate
Identifier 2004–NM–219–AD; Amendment
39–14287; AD 2005–19–22]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A330–322, –341, and –342 Airplanes;
and Airbus Model A340–200 and –300
Series Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for certain
Airbus Model A330–322, –341, and
–342 airplanes, and Model A340–200
and –300 series airplanes. This AD
requires modifying the left and right
ram air outlets of the two air
conditioning packs. The modification
includes replacing the old air outlet
assembly with a new air outlet
assembly, and modifying the web. This
AD results from a report of fatigue
cracks that initiated in the duct
structure of the ram air outlet, which is
adjacent to the hydraulics compartment.
We are issuing this AD to prevent
fatigue cracks in the duct structure of
the ram air outlet, which could lead to
hot air damage and consequent loss of
function of the hydraulics systems.
DATES: Effective October 7, 2005.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of October 7, 2005.
We must receive comments on this
AD by November 21, 2005.
ADDRESSES: Use one of the following
addresses to submit comments on this
AD.
• DOT Docket Web site: Go to
https://dms.dot.gov and follow the
instructions for sending your comments
electronically.
• Government-wide rulemaking Web
site: Go to https://www.regulations.gov
and follow the instructions for sending
your comments electronically.
• Mail: Docket Management Facility;
U.S. Department of Transportation, 400
Seventh Street SW., Nassif Building,
room PL–401, Washington, DC 20590.
• Fax: (202) 493–2251.
• Hand Delivery: Room PL–401 on
the plaza level of the Nassif Building,
400 Seventh Street SW., Washington,
DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
Contact Airbus, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France,
for service information identified in this
AD.
Tim
Backman, Aerospace Engineer,
International Branch, ANM–116, FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington
98055–4056; telephone (425) 227–2797;
fax (425) 227–1149.
FOR FURTHER INFORMATION CONTACT:
SUPPLEMENTARY INFORMATION:
Discussion
´ ´
The Direction Generale de l’Aviation
Civile (DGAC), which is the
airworthiness authority for France,
notified us that an unsafe condition may
exist for certain Airbus Model A330–
322, –341, and –342 airplanes, and
Model A340–200 and –300 series
airplanes. The DGAC advises that
fatigue cracks have been found that
initiated in the duct structure of the ram
air outlet, which is adjacent to the
hydraulics compartment. These fatigue
cracks were found on airplanes that had
been modified with an ‘‘adaptation
solution’’ that was intended to prevent
cracks and provide better thermal
insulation. However, analyses showed
that the adaptation solution did not
prevent cracks that initiate after the
12,000 flight-cycle threshold. Cracks in
the duct structure could propagate, and
certain rivet heads could shear from the
inside. Either condition could cause the
air outlet to rupture and lead to hot air
being blown into the hydraulics bay.
This condition, if not corrected, could
result in hot air damage and consequent
loss of function of the hydraulics
systems.
Relevant Service Information
Airbus has issued the service
bulletins listed in the following table.
AIRBUS SERVICE BULLETINS
Airbus service bulletin—
Revision
A330–53–3132 ..........................................................
A340–53–4139 ..........................................................
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15:53 Sep 21, 2005
Jkt 205001
PO 00000
02
02
Frm 00017
Dated
For model—
April 26, 2004 ..........
April 26, 2004 ..........
Fmt 4700
Sfmt 4700
55529
A330–322, –341, and –342 airplanes.
A340–200 and –300 series airplanes
E:\FR\FM\22SER1.SGM
22SER1
]]>Agencies
[Federal Register Volume 70, Number 183 (Thursday, September 22, 2005)]
[Rules and Regulations]
[Pages 55524-55529]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-18783]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2002-NM-66-AD; Amendment 39-14289; AD 2005-19-24]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 727 Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: This amendment supersedes an existing airworthiness directive
(AD), applicable to all Boeing Model 727 series airplanes, that
currently requires repetitive pre-modification inspections to detect
cracks in the forward support fitting of the number 1 and number 3
engines; and repair, if necessary. That AD also provides for an
optional high frequency eddy current inspection, and, if possible,
modification of the fastener holes; and various follow-on actions;
which would terminate the repetitive pre-modification inspections. This
amendment expands the area to be inspected; requires accomplishment of
the previously optional (and subsequently revised) modification, which
terminates certain repetitive inspections; and adds repetitive post-
modification inspections to detect cracking of the fastener holes, and
corrective actions if necessary. The actions specified by this AD are
intended to prevent fatigue cracking of the forward support fitting of
the number 1 and number 3 engines, which could result in failure of the
support fitting and consequent separation of the engine from the
airplane. This action is
[[Page 55525]]
intended to address the identified unsafe condition.
DATES: Effective October 27, 2005.
The incorporation by reference of Boeing Service Bulletin 727-
54A0010, Revision 6, including Appendix A, dated August 23, 2001, as
listed in the regulations, is approved by the Director of the Federal
Register as of October 27, 2005.
The incorporation by reference of Boeing Service Bulletin 727-
54A0010, Revision 4, dated January 30, 1997, as listed in the
regulations, was approved previously by the Director of the Federal
Register as of March 18, 1997 (62 FR 9359, March 3, 1997).
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) by superseding AD 97-05-08,
amendment 39-9952 (62 FR 9359, March 3, 1997), which is applicable to
all Boeing Model 727 series airplanes, was published in the Federal
Register on May 1, 2003 (68 FR 23231). The action proposed to continue
to require repetitive pre-modification inspections to detect cracks in
the forward support fitting of the number 1 and number 3 engines, and
repair if necessary. The action also proposed to expand the area to be
inspected; require accomplishment of the previously optional (and
subsequently revised) modification, which would terminate certain
repetitive inspections; and add repetitive post-modification
inspections to detect cracking of the fastener holes, and corrective
actions if necessary.
Comments
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the comments received.
Requests To Revise the Applicability
One commenter requests that the applicability of the proposed AD be
revised to apply only to Boeing Model 727 airplanes equipped with
fittings having part number (P/N) 65-18722-xx. The commenter states
that its Model 727-100 fleet does not include any airplanes equipped
with fittings having that P/N. Because it changed the affected fittings
during a re-engine modification in accordance with Supplemental Type
Certificate (STC) SA8472SW, it was granted an alternate method of
compliance (AMOC) for AD 97-05-08. The commenter asserts that revising
the proposed applicability will prevent operators that do not have the
affected fittings installed from having to request an AMOC for the
requirements of the proposed AD.
Another commenter requests that a statement be added to the
proposed AD to exempt airplanes modified in accordance with STC
SA4363NM. The commenter asserts that inclusion of this statement will
make it perfectly clear to operators whether or not they are in
compliance with the AD.
We acknowledge the commenters' concern and, as we state in
paragraph (t)(2) of this AD, AMOCs previously approved according to AD
97-05-08 are acceptable for compliance with the corresponding
requirements of this AD. These AMOCs address the commenter's concern.
We find that no further clarifications are necessary and have made no
change to the final rule in this regard.
Request To Add Language Specific to Airplanes With ``Hush Kit'' STCs
Installed
A third commenter requests that specific language be included in
the final rule stating that airplanes modified in accordance with STCs
SA3993NM, SA4833NM, SA5839NM, and ST00350AT may be inspected and
modified in accordance with Boeing Service Bulletin 727-54A0010,
Revision 6, without change. (Boeing Service Bulletin 727-54A0010,
Revision 6, dated August 23, 2001, was referenced in the proposed AD as
the appropriate source of service information for accomplishing the new
actions). These STCs install noise suppression modification equipment
(hush kits) on Model 727 airplanes. The commenter states that including
this information in the AD, in lieu of making operators request AMOCs,
will avoid confusion among operators with airplanes equipped with these
STCs. The commenter submitted substantiating data to support its
request.
We do not agree. The static strength data analysis of the affected
structure submitted was not sufficient to show that the commenter's
request would result in an acceptable level of safety. Damage tolerance
assessment is needed to determine if the inspections and modifications
described in Boeing Service Bulletin 727-54A0010, Revision 6, are
appropriate for airplanes modified in accordance with these STCs. In
this case, the ability to inspect the affected area and changes in
fatigue stress levels need to be addressed. Additionally, the
inspections and modifications specified in the service bulletin
specifically address only affected original equipment manufacturer
configurations. However, as we explained previously, we will consider
requests for AMOCs submitted with sufficient technical justification to
support the request. We have made no change to the final rule regarding
this issue.
Request To Change the Method of Inspection
Another commenter, the manufacturer, requests that we revise
paragraphs (d)(1) and (d)(3) of the proposed AD to revise the method of
inspection. Specifically, the commenter recommends revising ``* * * If
any corrosion is found, before further flight, remove the corrosion in
accordance with Figure 5 of the service bulletin, and perform a general
visual inspection to detect cracking * * *'' to read ``* * * If any
corrosion is found, before further flight, remove the corrosion in
accordance with Figure 5 of the service bulletin, and perform a HFEC
inspection to detect cracking * * *.'' The commenter asserts that the
high frequency eddy current (HFEC) inspection is a better method than a
surveillance inspection and will provide an adequate level of safety by
enabling operators to find small cracks.
We partially agree with the commenter. We find that an HFEC
inspection should be accomplished after removal of corrosion. However,
we do not agree that it is necessary to revise paragraphs (d)(1) and
(d)(3) of this final rule as requested. Paragraphs (d)(1) and (d)(3)
require any corrosion found to be removed in accordance with Figure 5
of Boeing Service Bulletin 727-54A0010, Revision 6, dated August 23,
2001. Step 5 of Figure 5 of the service bulletin includes procedures
for doing an HFEC inspection for cracks and repairing any cracks found
once the corrosion has been identified and removed from the affected
area. The general visual inspection required by paragraphs (d)(1) and
(d)(3) follows the instructions given in Figure 1, Step 2, of the
service bulletin. We find that no change to the final rule is necessary
regarding this issue.
[[Page 55526]]
Request To Refer Specifically to Post-Modification Inspections
The same commenter also requests that paragraph (m) of the proposed
AD be revised to refer to the post-modification inspections in Revision
5 of Boeing Alert Service Bulletin 727-54A0010, dated February 15,
2001. Specifically, the commenter recommends revising ``* * *
Inspections done before the effective date of this AD in accordance
with Boeing Alert Service Bulletin 727-54A0010, Revision 5, dated
February 15, 2001, are acceptable for compliance with the corresponding
inspection requirements of this paragraph * * *.'' to ``* * *
Inspections done before the effective date of this AD in accordance
with Part III of the Accomplishment Instructions of Boeing Alert
Service Bulletin 727-54A0010, Revision 5, dated February 15, 2001, are
acceptable for compliance with the corresponding inspection
requirements of this paragraph * * *.'' The commenter believes that,
for airplanes that have accomplished the modification, only the repeat
post-modification inspection requirements of Revision 5 of the service
bulletin provide an equivalent level of safety for the fleet.
We agree with the request for the reason provided by the commenter.
It was our intent to refer specifically to Part III of the
Accomplishment Instructions of Revision 5 of the service bulletin in
paragraph (m). Therefore, we have revised paragraph (m) of this final
rule to specifically refer to Part III of the Accomplishment
Instructions of Revision 5 of the service bulletin for accomplishment
of post-modification inspections done before the effective date of the
AD.
Explanation of Additional Changes to the Proposed AD
Boeing has received a Delegation Option Authorization (DOA). We
have revised this final rule to delegate the authority to approve an
alternative method of compliance for any repair required by this AD to
the Authorized Representative for the Boeing DOA Organization rather
than the Designated Engineering Representative (DER). Accordingly, we
have added paragraph (t)(3) to this final rule and revised the wording
of paragraphs (h)(1) and (i) of this AD. We have also revised the
wording of paragraph (t)(1) of this final rule (specified as paragraph
(s)(1) in the proposed AD) for reasons discussed under ``Changes to 14
CFR part 39/Effect on the AD.''
Because the language in Note 6 of the proposed AD is regulatory in
nature, that note has been redesignated as paragraph (r) of this final
rule. We have re-identified subsequent notes and paragraphs
accordingly.
Conclusion
After careful review of the available data, including the comments
noted above, the FAA has determined that air safety and the public
interest require the adoption of the rule with the changes previously
described. The FAA has determined that these changes will neither
increase the economic burden on any operator nor increase the scope of
the AD.
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 AMOCs. Because we have
now included this material in part 39, only the office authorized to
approve AMOCs is identified in each individual AD. However, for clarity
and consistency in this final rule, we have retained the language of
the NPRM regarding that material, except for the revisions to certain
language discussed previously.
Change to Labor Rate Estimate and Airplane Fleet Data
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.
We have also revised the cost impact information to more accurately
describe the number of airplanes of the affected design in the current
worldwide and U.S. fleets.
Cost Impact
There are approximately 1,009 airplanes of the affected design in
the worldwide fleet. The FAA estimates that 587 airplanes of U.S.
registry will be affected by this AD.
We provide the following cost estimates for this AD:
----------------------------------------------------------------------------------------------------------------
Average
Action Work hours labor rate Cost of Cost per Cost for the U.S.
per hour parts airplane fleet
----------------------------------------------------------------------------------------------------------------
AD 97-05-08 inspections, per 2 $65 $0 $130 $76,310, per
inspection cycle. inspection cycle.
Inspections before structural 14 65 0 910 534,170, per
rework, per inspection cycle. inspection cycle.
Structural rework................... 7 65 7,875 8,330 4,889,710.
Inspections after structural rework, 12 65 0 780 457,860, per
per inspection cycle. inspection cycle.
----------------------------------------------------------------------------------------------------------------
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
[[Page 55527]]
``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 removing amendment 39-9952 (62 FR 9359,
March 3, 1997), and by adding a new airworthiness directive (AD),
amendment 39-14289, to read as follows:
2005-19-24 Boeing: Amendment 39-14289. Docket 2002-NM-66-AD.
Supersedes AD 97-05-08, Amendment 39-9952.
Applicability: All Model 727 series airplanes, certificated in
any category.
Note 1: This AD applies to each airplane identified in the
preceding applicability provision, regardless of whether it has been
modified, altered, or repaired in the area subject to the
requirements of this AD. For airplanes that have been modified,
altered, or repaired so that the performance of the requirements of
this AD is affected, the owner/operator must request approval for an
alternative method of compliance in accordance with paragraph (t)(1)
of this AD. The request should include an assessment of the effect
of the modification, alteration, or repair on the unsafe condition
addressed by this AD; and, if the unsafe condition has not been
eliminated, the request should include specific proposed actions to
address it.
Compliance: Required as indicated, unless accomplished
previously.
To prevent fatigue cracking of the forward support fitting of
the number 1 and number 3 engines, which could result in failure of
the support fitting and consequent separation of the engine from the
airplane, accomplish the following:
Restatement of Requirements of AD 97-05-08
Inspections
(a) Within 100 days or 600 flight cycles after March 18, 1997
(the effective date of AD 97-05-08, amendment 39-9952), whichever
occurs first, accomplish paragraphs (a)(1), (a)(2), and (a)(3) of
this AD, in accordance with Boeing Service Bulletin 727-54A0010,
Revision 4, dated January 30, 1997.
(1) Perform a visual inspection to detect cracks of the upper
and lower flanges, and the vertical web of the forward support
fitting of the number 1 and number 3 engines, in accordance with
Part 1--Pre-Modification Inspections of the Accomplishment
Instructions of the service bulletin.
(2) Perform a high frequency eddy current (HFEC) inspection to
detect cracks of the forward flange of the support fitting adjacent
to the collars of two fasteners of the number 1 and number 3
engines, in accordance with Part 1--Pre-Modification Inspections of
the Accomplishment Instructions of the service bulletin.
(3) Perform a detailed inspection to detect cracks of the upper
and lower flanges adjacent to six fasteners of the fitting of the
number 1 and number 3 engines, in accordance with Part 1--Pre-
Modification Inspections of the Accomplishment Instructions of the
service bulletin.
Note 2: 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.''
(b) If no crack is detected during the inspections required by
paragraph (a) of this AD, repeat those inspections thereafter at
intervals not to exceed 100 days or 600 flight cycles, whichever
occurs first, until the initial inspections required by paragraph
(d) of this AD have been accomplished.
(c) If any crack is detected during any inspection required by
paragraph (a) of this AD, prior to further flight, repair the
forward support fitting in accordance with a method approved by the
Manager, Seattle Aircraft Certification Office (ACO), FAA.
New Requirements of This AD
Note 3: Where there are differences between the service bulletin
and this AD, this AD prevails.
Inspections: All Airplanes
(d) For all airplanes: Within 600 flight cycles or 100 days
after the effective date of this AD, whichever occurs first, inspect
the forward support fitting of the number 1 and number 3 engines, as
specified in paragraphs (d)(1), (d)(2), (d)(3), (d)(4), and (d)(5)
of this AD, in accordance with Part I of the Accomplishment
Instructions of Boeing Service Bulletin 727-54A0010, Revision 6,
dated August 23, 2001. Accomplishment of these initial inspections
terminates the inspection requirements of paragraphs (a) and (b) of
this AD.
(1) Perform a general visual inspection to detect corrosion and
cracking of the fittings in areas inboard of the side of the body,
in accordance with Figure 1 of the service bulletin. If any
corrosion is found, before further flight, remove the corrosion by
accomplishing all of the actions in and in accordance with Figure 5
of the service bulletin, and then perform a general visual
inspection to detect cracking of the area, in accordance with the
service bulletin.
Note 4: For the purposes of this AD, a general visual inspection
is: ``A visual examination of an interior or exterior area,
installation, or assembly to detect obvious damage, failure, or
irregularity. This level of inspection is made from within touching
distance unless otherwise specified. A mirror may be necessary to
ensure visual access to all surfaces in the inspection area. This
level of inspection is made under normally available lighting
conditions such as daylight, hangar lighting, flashlight, or
droplight and may require removal or opening of access panels or
doors. Stands, ladders, or platforms may be required to gain
proximity to the area being checked.''
(2) Perform an HFEC inspection to detect cracking of the upper
and lower horizontal flanges and post tangs of the fittings from
inside the airplane, in accordance with Figure 1 of the service
bulletin.
(3) Perform a general visual inspection to detect cracking and
corrosion of the fittings in areas outboard of the side of the body,
in accordance with Figure 1 of the service bulletin. If any
corrosion is found, before further flight, remove the corrosion by
accomplishing all of the actions in and in accordance with Figure 5
of the service bulletin, and perform a general visual inspection to
detect cracking of the area, in accordance with the service
bulletin.
(4) Perform a detailed inspection to detect cracking and
corrosion of the web in areas outboard of the side of the body, in
accordance with Figure 1 of the service bulletin. If any corrosion
is found, before further flight, remove the corrosion in accordance
with Figure 5 of the service bulletin, and perform thickness
measurements and detailed and HFEC inspections of the vertical web
inboard and outboard of the side of the body to detect corrosion and
cracking, in accordance with Figure 2 of the service bulletin. If
the web thickness is less than 0.130 inch, do paragraph (i) of this
AD.
(5) Perform detailed and HFEC inspections to detect cracking of
the upper and lower horizontal flanges at the side of the body, in
accordance with Figure 1 of the service bulletin.
Additional Inspections: Group 2 Airplanes
(e) For Group 2 airplanes, as identified in Boeing Service
Bulletin 727-54A0010, Revision 6, dated August 23, 2001: Within 600
flight cycles or 100 days after the effective date of this AD,
whichever occurs first, inspect the forward support fitting of the
number 1 and number 3 engines at the
[[Page 55528]]
firewall to detect cracking, as specified in paragraphs (e)(1),
(e)(2), (e)(3), and (e)(4) of this AD, in accordance with Part I of
the Accomplishment Instructions of the service bulletin.
(1) Perform a detailed inspection to detect cracking of the aft
side of the upper horizontal flange, in accordance with Figure 1 of
the service bulletin.
(2) Perform a low frequency eddy current (LFEC) or an open hole
HFEC inspection to detect cracking of the aft side of the upper
horizontal flange, in accordance with Figure 1 of the service
bulletin.
(3) Perform a detailed inspection to detect cracking of the aft
side of the lower horizontal flange, in accordance with Figure 1 of
the service bulletin.
(4) Perform an HFEC inspection to detect cracking of the aft
side of the lower horizontal flange, in accordance with Figure 1 of
the service bulletin.
No Cracking Found: Follow-on Inspections, All Airplanes
(f) For all airplanes: If no cracking is found during any
inspection required by paragraph (d) of this AD, repeat the
applicable inspections within the applicable intervals specified in
paragraph 1.E., Table 1, of Boeing Service Bulletin 727-54A0010,
Revision 6, dated August 23, 2001, until the modification required
by paragraph (j) of this AD has been done.
No Cracking Found: Additional Follow-on Inspections, Group 2 Airplanes
(g) For Group 2 airplanes only: If no cracking is found during
the inspections required by paragraph (e) of this AD, repeat the
inspections on the upper and lower outboard flange at the firewall
within the applicable intervals specified in paragraph 1.E., Table
1, of Boeing Service Bulletin 727-54A0010, Revision 6, dated August
23, 2001.
(1) Repeat the inspections of the upper outboard flange at the
firewall until the modification required by paragraph (j) of this AD
has been done.
(2) Repeat the inspections of the lower outboard flange at the
firewall indefinitely. There is no terminating action for the
inspections of this area.
Note 5: Boeing Service Bulletin 727-54A0010, Revision 6, dated
August 23, 2001, does not provide instructions for modifying the
fastener holes of the lower outboard flange at the firewall.
Cracking Found: Any Airplane
(h) For any airplane: If any crack is found during any
inspection required by paragraph (d), (e), (f), or (g) of this AD,
before further flight, do the actions specified in either paragraph
(h)(1) or (h)(2) of this AD.
(1) Replace or repair the fitting in accordance with a method
approved by the Manager, Seattle ACO; or according to data meeting
the certification basis of the airplane approved by an Authorized
Representative for the Boeing Delegation Option Authorization (DOA)
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; or
(2) Do the modification specified in paragraph (j) of this AD.
Web Thickness Less Than 0.130 Inch: Any Airplane
(i) For any airplane: If the web thickness measured during
accomplishment of paragraph (d)(4) of this AD is less than 0.130
inch, before further flight, replace or repair the fitting in
accordance with a method approved by the Manager, Seattle ACO; or
according to data meeting the certification basis of the airplane
approved by an Authorized Representative for the Boeing DOA
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.
Modification
(j) Except as required by paragraphs (h), (i), and (q) of this
AD: Within 3,000 flight cycles or 24 months after the effective date
of this AD, whichever occurs first, modify the fastener holes, in
accordance with Part II of the Accomplishment Instructions of Boeing
Service Bulletin 727-54A0010, Revision 6, dated August 23, 2001.
Accomplishment of the modification terminates the repetitive
inspections required by paragraphs (f) and (g)(1) of this AD.
Modification in Accordance With Prior Service Bulletin Revision
(k) For airplanes modified before the effective date of this AD
in accordance with Boeing Service Bulletin 727-54A0010, Revision 4,
dated January 30, 1997: Paragraph (j) of this AD requires
accomplishment of additional procedures in accordance with Revision
6 of the service bulletin. To the extent that certain modification
procedures were performed in accordance with Revision 4, those
actions do not need to be repeated when performing the modification
required in paragraph (j) of this AD.
(l) A modification done before the effective date of this AD in
accordance with Boeing Alert Service Bulletin 727-54A0010, Revision
5, dated February 15, 2001, is acceptable for compliance with the
requirements of paragraph (j) of this AD.
Post-Modification Inspections
(m) Inspect as specified in paragraphs (m)(1), (m)(2), and (n)
of this AD, as applicable, to detect cracking and corrosion, in
accordance with Part III of the Accomplishment Instructions of
Boeing Service Bulletin 727-54A0010, Revision 6, dated August 23,
2001. Inspections done before the effective date of this AD in
accordance with Part III of Boeing Alert Service Bulletin 727-
54A0010, Revision 5, dated February 15, 2001, are acceptable for
compliance with the corresponding inspection requirements of this
paragraph.
(1) For all airplanes: Do an open hole HFEC inspection of the
fastener holes in the forward support fitting of the number 1 and
number 3 engines, at the locations shown in Figure 4 of the service
bulletin.
(2) For Group 2 airplanes: Do an open hole HFEC inspection of
the fastener holes in the forward support fitting of the number 1
and number 3 engines, at the locations shown in Figure 4 of the
service bulletin.
(n) Perform the inspections specified in paragraph (m) of this
AD at the later of the times specified in paragraphs (n)(1) and
(n)(2) of this AD.
(1) Within 3,000 flight cycles or 24 months, whichever occurs
first, after accomplishment of the modification required by
paragraph (j) of this AD.
(2) Within 600 flight cycles or 100 days, whichever occurs
first, after the effective date of this AD.
Follow-On/Corrective Actions
(o) If no cracking is found during any inspection required by
paragraph (m) of this AD: Repeat the inspections specified in
paragraph (m) of this AD thereafter within the applicable intervals
specified in paragraph 1.E., Table 1, of Boeing Service Bulletin
727-54A0010, Revision 6, dated August 23, 2001. Accomplishment of
the modification specified in paragraph (j) of this AD does not
terminate the requirement to repetitively perform the post-
modification inspections specified in Part III of the service
bulletin.
(p) If any cracking is detected during any inspection required
by paragraph (m) of this AD: Before further flight, repair in
accordance with Boeing Service Bulletin 727-54A0010, Revision 6,
dated August 23, 2001; except as required by paragraph (q) of this
AD.
Exception to Corrective Actions
(q) Where Boeing Service Bulletin 727-54A0010, Revision 6, dated
August 23, 2001, specifies to contact Boeing for appropriate action:
Before further flight, replace or repair the fitting in accordance
with a method approved by the Manager, Seattle ACO; or according to
data meeting the certification basis of the airplane approved by an
Authorized Representative for the Boeing DOA 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.
Reporting Not Required
(r) Boeing Service Bulletin 727-54A0010, Revision 6, dated
August 23, 2001, recommends that operators report inspection results
to the manufacturer; however, this AD does not contain this
requirement.
Parts Installation
(s) As of the effective date of this AD, no person may install a
forward support fitting on any airplane, unless it has been
inspected and modified, as applicable, in accordance with the
requirements of this AD.
Alternative Methods of Compliance
(t)(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) AMOCs previously approved according to AD 97-05-08 are
acceptable for
[[Page 55529]]
compliance with the corresponding requirements of this AD.
(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 DOA 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.
Note 6: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Seattle ACO.
Special Flight Permits
(u) Special flight permits may be issued according to sections
21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197
and 21.199) to operate the airplane to a location where the
requirements of this AD can be accomplished.
Incorporation by Reference
(v) Unless otherwise specified in this AD, the actions must be
done in accordance with Boeing Service Bulletin 727-54A0010,
Revision 4, dated January 30, 1997; and Boeing Service Bulletin 727-
54A0010, Revision 6, including Appendix A, dated August 23, 2001; as
applicable.
(1) The incorporation by reference of Boeing Service Bulletin
727-54A0010, Revision 6, including Appendix A, dated August 23,
2001, is approved by the Director of the Federal Register in
accordance with 5 U.S.C. 552(a) and 1 CFR part 51.
(2) The incorporation by reference of Boeing Service Bulletin
727-54A0010, Revision 4, dated January 30, 1997, was approved
previously by the Director of the Federal Register as of March 18,
1997 (62 FR 9359, March 3, 1997).
(3) 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 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.
Effective Date
(w) This amendment becomes effective on October 27, 2005.
Issued in Renton, Washington, on September 8, 2005.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-18783 Filed 9-21-05; 8:45 am]
BILLING CODE 4910-13-P
