Airworthiness Directives; Boeing Model 727 Airplanes, 12120-12124 [05-4826]
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12120
Federal Register / Vol. 70, No. 47 / Friday, March 11, 2005 / Rules and Regulations
Washington 98055–4056; telephone
(425) 917–6441; fax (425) 917–6590.
SUPPLEMENTARY INFORMATION: On
January 31, 2005, the FAA issued AD
2005–03–11, amendment 39–13967 (70
FR 7174, February 11, 2005), for certain
Boeing Model 767 series airplanes. The
AD requires repetitive detailed and
eddy current inspections of the aft
pressure bulkhead for damage and
cracking, and repair if necessary. The
AD also requires one-time detailed and
high frequency eddy current inspections
of any ‘‘oil-can’’ located on the aft
pressure bulkhead, and related
corrective actions if necessary.
As published, that final rule
incorrectly specified the AD number in
a single location in the AD as ‘‘2005–
NM–03–11’’ instead of ‘‘2005–03–11.’’
No other part of the regulatory
information has been changed;
therefore, the final rule is not
republished in the Federal Register.
The effective date of this AD remains
March 18, 2005.
§ 39.13
[Corrected]
In the Federal Register of February 11,
2005, on page 7175, in the first column,
paragraph 2. of PART 39—
AIRWORTHINESS DIRECTIVES is
corrected to read as follows:
*
*
*
*
*
I
2005–03–11 Boeing: Amendment 39–13967.
Docket No. FAA–2004–19446;
Directorate Identifier 2004–NM–130–AD.
*
*
*
*
*
Issued in Renton, Washington, on February
28, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 05–4825 Filed 3–10–05; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2004–19530; Directorate
Identifier 2002–NM–274–AD; Amendment
39–14008; AD 2005–05–19]
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 superseding an
existing airworthiness directive (AD),
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which applies to certain Boeing Model
727 airplanes. That AD currently
requires repetitive detailed inspections
to detect cracking, corrosion, and
existing stop-drilled repairs of cracking
in the upper chord of the rear spar of the
wing; and repair if necessary. This new
AD requires new repetitive inspections
to detect cracks, corrosion, minor
surface defects, and existing stop-drilled
repairs of cracks in the upper and lower
chords of the front and rear spars of the
wing; and repair if necessary. This AD
is prompted by our determination that
further rulemaking action is necessary
to require additional actions specified in
the referenced service bulletin. We are
issuing this AD to prevent structural
failure of the wing and fuel leaks in the
airplane due to stress corrosion cracking
of the wing spar chords.
DATES: This AD becomes effective April
15, 2005.
On December 18, 2002 (67 FR 71808,
December 3, 2002), the Director of the
Federal Register approved the
incorporation by reference of Boeing
Alert Service Bulletin 727–57A0145,
Revision 2, dated October 24, 2002.
ADDRESSES: For service information
identified in this AD, contact Boeing
Commercial Airplanes, P.O. Box 3707,
Seattle, Washington 98124–2207.
Docket: The AD docket contains the
proposed AD, comments, and any final
disposition. You can examine the 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 U.S. Department of Transportation,
400 Seventh Street SW, room PL–401,
Washington, DC. This docket number is
FAA–2004–19530; the directorate
identifier for this docket is 2002–NM–
274–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: The FAA
proposed to amend part 39 of the
Federal Aviation Regulations (14 CFR
Part 39) with an AD to supersede AD
2002–24–05, amendment 39–12970 (67
FR 71808, December 3, 2002). The
existing AD applies to certain Boeing
Model 727 airplanes. The proposed AD
was published in the Federal Register
on November 5, 2004 (69 FR 64506), to
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require new repetitive inspections to
detect cracks, corrosion, minor surface
defects, and existing stop-drilled repairs
of cracks in the upper and lower chords
of the front and rear spars of the wing;
and repair if necessary.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the comment that has been
submitted on the proposed AD. The
commenter supports the proposed AD.
Explanation of Change to Model
Designation
We have revised the subject heading
of the existing AD to identify model
designations as published in the most
recent type certificate data sheet for the
affected models.
Changes to Delegation Authority
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).
Conclusion
We have carefully reviewed the
available data, including the comment
that has been submitted, and
determined that air safety and the
public interest require adopting the AD
with the change described previously.
We have determined that this change
will neither increase the economic
burden on any operator nor increase the
scope of the AD.
Costs of Compliance
There are about 1,426 airplanes of the
affected design in the worldwide fleet.
This AD will affect about 946 airplanes
of U.S. registry.
For Group 1 airplanes identified in
the service bulletin, the actions (Part 1
of the Accomplishment Instructions of
the service bulletin) that are required by
AD 2002–24–05 and retained in this AD
take about 8 work hours per airplane, at
an average labor rate of $65 per work
hour. Based on these figures, the
estimated cost of the currently required
actions is $520 per airplane.
The following table provides the
estimated costs for U.S. operators to
comply with the new actions required
by this AD. The average labor rate is $65
per work hour.
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Federal Register / Vol. 70, No. 47 / Friday, March 11, 2005 / Rules and Regulations
ESTIMATED COSTS
For airplanes identified in the service bulletin as—
Actions in—
Group 1 ...........................................................................
Part 2 of the Accomplishment
service bulletin.
Part 3 of the Accomplishment
service bulletin.
Part 4 of the Accomplishment
service bulletin.
Part 8 of the Accomplishment
service bulletin.
Part 9 of the Accomplishment
service bulletin.
Part 5 of the Accomplishment
service bulletin.
Part 6 of the Accomplishment
service bulletin.
Group 1 ...........................................................................
Group 1 ...........................................................................
Group 1 ...........................................................................
Group 1 ...........................................................................
Group 2 ...........................................................................
Group 2 ...........................................................................
Authority for This Rulemaking
Instructions of the
30
$1,950
Instructions of the
21
1,365
Instructions of the
68
4,420
Instructions of the
8
520
Instructions of the
30
1,950
Instructions of the
52
3,380
Instructions of the
110
7,150
We prepared a regulatory evaluation
of the estimated costs to comply with
this AD. See the ADDRESSES section for
a location to examine the regulatory
evaluation.
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. Subtitle VII,
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in Subtitle VII,
Part A, Subpart III, Section 44701,
‘‘General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
I
Regulatory Findings
§ 39.13
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.
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Per airplane
cost, per
inspection
cycle—
Work hours—
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
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.
Unsafe Condition
(d) This AD was prompted by our
determination that further rulemaking action
is necessary to require additional actions
specified in the referenced service bulletin.
We are issuing this AD to prevent structural
failure of the wing and fuel leaks in the
airplane due to stress corrosion cracking of
the wing spar chords.
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 References
(f) The term ‘‘the service bulletin,’’ as used
in this AD, means Boeing Alert Service
Bulletin 727–57A0145, Revision 2, dated
October 24, 2002.
Inspection Requirements of AD 2002–24–05,
Amendment 39–12970
Inspection
(g) For airplanes specified as ‘‘Group 1’’
airplanes in the service bulletin: Within 20
years after the date of manufacture or within
I 2. The FAA amends § 39.13 by
90 days after December 18, 2002 (the
removing amendment 39–12970 (67 FR
effective date of AD 2002–24–05, amendment
71808, December 3, 2002), and by adding 39–12970), whichever occurs later, perform
an external detailed inspection for cracking,
the following new airworthiness
corrosion, and existing stop-drilled repairs of
directive (AD):
cracking in the upper chord on the rear spar
2005–05–19 Boeing: Amendment 39–14008.
from Wing Butt Line (WBL) 70.5 through
Docket No. FAA–2004–19530;
WBL 249.3, per the service bulletin,
Directorate Identifier 2002–NM–274–AD. paragraph 3.B, ‘‘Work Instructions,’’ Part 1.
Thereafter, repeat the inspection at intervals
Effective Date
not to exceed 2 years.
(a) This AD becomes effective April 15,
Note 1: For the purposes of this AD, a
2005.
detailed inspection is ‘‘an intensive
Affected ADs
examination of a specific item, installation,
or assembly to detect damage, failure, or
(b) This AD supersedes AD 2002–24–05,
irregularity. Available lighting is normally
amendment 39–12970.
supplemented with a direct source of good
Applicability
lighting at an intensity deemed appropriate.
(c) This AD applies to Boeing Model 727,
Inspection aids such as mirrors, magnifying
727C, 727–100, –100C, –200, and –200F
lenses, etc., may be necessary. Surface
series airplanes, line numbers 1 through 1832 cleaning and elaborate procedures may be
inclusive; certificated in any category.
required.’’
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Federal Register / Vol. 70, No. 47 / Friday, March 11, 2005 / Rules and Regulations
New Actions Required by This AD
Inspections Specified in Parts 2 Through 6,
and 8 and 9 of the Service Bulletin
(h) Accomplish the applicable
inspection(s) specified in paragraphs (h)(1)
through (h)(7) of this AD at the later of the
applicable times specified in the
‘‘Threshold’’ and ‘‘Grace Period’’ columns in
Table 1 of this AD, and repeat the
inspection(s) at the time specified in the
‘‘Repetitive Interval’’ column of Table 1 of
this AD. Accomplishment of the inspection
required by paragraph (h)(1) of this AD
terminates the repetitive inspection
requirements of paragraph (g) of this AD.
TABLE 1.—COMPLIANCE TIMES FOR INSPECTIONS SPECIFIED IN PARTS 2 THROUGH 6, AND 8 AND 9 OF SERVICE BULLETIN
For airplanes identified in
the service bulletin as—
Threshold—
Grace period—
Repetitive interval—
Do—
(1) Group 1 ........................
Before 20 years since the
date of issuance of the
original Airworthiness
Certificate or the date of
issuance of the original
Export Certificate of Airworthiness.
Within 1 year after the effective date of this AD.
None ..................................
(2) Group 1 ........................
Before 20 years since the
date of issuance of the
original Airworthiness
Certificate or the date of
issuance of the Original
Export Certificate of Airworthiness.
Within 2 years after the effective date of this AD.
At intervals not to exceed
2 years.
(3) Group 1 ........................
Before 20 years since the
date of issuance of the
original Airworthiness
Certificate or the date of
issuance of the original
Export Certificate of Airworthiness.
Within 4 years after the effective date of this AD.
At intervals not to exceed
4 years.
(4) Group 1 ........................
Within 2 years after doing
the actions required by
paragraph (h)(1) of this
AD.
None ..................................
At intervals not to exceed
2 years.
A high frequency eddy current (HFEC) inspection
and detailed inspection
of the upper chord the
rear spar from WBL 70.5
to the wing tip for
cracks, corrosion, minor
surface defects, and existing stop-drilled repairs
of cracking, in accordance with paragraph
3.B., Work Instructions,
Part 2, of the Accomplishment Instructions of
the service bulletin.
A detailed inspection of
the upper and lower
chord of the front spar
and the lower chord of
the rear spar from WBL
70.5 to the wing tip for
cracks, corrosion, minor
surface defects, and existing stop-drilled repairs
of cracking (initial inspection only), in accordance with paragraph
3.B., Work Instructions,
Part 3, of the Accomplishment Instructions of
the service bulletin.
An HFEC inspection of the
upper and lower chords
of the rear spar from
WBL 70.5 to the wing tip
for cracks, corrosion,
minor surface defects,
and existing stop-drilled
repairs of cracking (initial inspection only), in
accordance with paragraph 3.B., Work Instructions, Part 4, of the
Accomplishment Instructions of the service bulletin.
A detailed inspection of
the upper chord of the
rear spar WBL 70.5 to
the wing tip for cracks,
corrosion, minor surface
defects, and existing
stop-drilled repairs of
cracking (initial inspection only), in accordance
with paragraph 3.B.,
Work Instructions, Part
8, of the Accomplishment Instructions of the
service bulletin.
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Federal Register / Vol. 70, No. 47 / Friday, March 11, 2005 / Rules and Regulations
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TABLE 1.—COMPLIANCE TIMES FOR INSPECTIONS SPECIFIED IN PARTS 2 THROUGH 6, AND 8 AND 9 OF SERVICE
BULLETIN—Continued
For airplanes identified in
the service bulletin as—
Threshold—
Grace period—
Repetitive interval—
Do—
(5) Group 1 ........................
Within 4 years after doing
the actions required by
paragraph (h)(1) of this
AD.
None ..................................
At intervals not to exceed
4 years.
(6) Group 2 ........................
Before 20 years since the
date of issuance of the
original Airworthiness
Certificate or the date of
issuance of the original
Export Certificate of Airworthiness.
Within 2 years after the effective date of this AD.
At intervals not to exceed
2 years.
(7) Group 2 ........................
Before 20 years since the
date of issuance of the
original Airworthiness
Certificate or the date of
issuance of the original
Export Certificate of Airworthiness.
Within 4 years after the effective date of this AD.
At intervals not to exceed
4 years.
An HFEC inspection of
doing the not to the
upper chord actions exceed 4 of the rear spar
required by years from
WBL 70.5 to paragraph
the wing tip for (h)(1) of
cracks, this AD corrosion, minor surface defects, and existing stopdrilled repairs of cracking (initial inspection
only), in accordance with
paragraph 3.B., Work Instructions, Part 9, of the
Accomplishment Instructions of the service bulletin.
An exterior detailed inspection of the upper
and lower chords of the
front and rear spars
from WBL 70.5 to the
wing tip for cracks, corrosion, minor surface
defects, and existing
stop-drilled repairs of
cracking (initial inspection only), in accordance
with paragraph 3.B.,
Work Instructions, Part
5, of the Accomplishment Instructions of the
service bulletin.
An HFEC inspection of the
upper and lower chords
of the front and rear
spars from WBL 70.5 to
the wing tip for cracks,
corrosion, minor surface
defects, and existing
stop-drilled repairs of
cracking (initial inspection only), in accordance
with paragraph 3.B.,
Work Instructions, Part
6, of the Accomplishment Instructions of the
service bulletin.
Corrective Actions
(i) If any crack, corrosion, or minor surface
defect is detected during any inspection
required by this AD, before further flight, do
the applicable corrective actions in
accordance with Part 7 of the
Accomplishment Instructions of the service
bulletin, except as provided by paragraph (j)
of this AD.
(j) If any crack or corrosion is detected
during any inspection required by this AD
that exceeds the limits specified in the
service bulletin, and the bulletin specifies to
contact Boeing for appropriate action: Before
further flight, repair in accordance with a
method approved by the Manager, Seattle
Aircraft Certification Office (ACO), FAA; or
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in accordance with data meeting the
certification basis of the airplane approved
by an Authorized Representative for the
Boeing Delegation Option Authorization
Organization who has been authorized by the
Manager, Seattle ACO, to make such
findings. For a repair method to be approved,
the approval must specifically reference this
AD.
(k) If any existing stop-drilled repair of
previous cracking is detected during any
inspection required by this AD, before further
flight, permanently repair crack in
accordance with paragraph 3.B., Work
Instructions, Part 7, paragraph 2., ‘‘Crack
Repair’’ of the Accomplishment Instructions
of the service bulletin.
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(l) Before further flight following any
inspection or repair required by this AD,
apply a wet layer of BMS 3–23 organic
corrosion inhibiting compound or Boeing
equivalent, in accordance with the
Accomplishment Instructions of the service
bulletin.
Alternative Methods of Compliance
(AMOCs)
(m)(1) The Manager, Seattle ACO, FAA,
has the authority to approve AMOCs for this
AD, if requested using the procedures found
in 14 CFR 39.19.
(2) Alternative methods of compliance,
approved previously in accordance with AD
2002–24–05, amendment 39–12970, are
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Federal Register / Vol. 70, No. 47 / Friday, March 11, 2005 / Rules and Regulations
approved as alternative methods of
compliance with 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
Delegation Option Authorization
Organization who has been authorized by the
Manager, Seattle ACO, to make such
findings. For a repair method to be approved,
the approval must specifically reference this
AD.
Material Incorporated by Reference
(n) You must use Boeing Alert Service
Bulletin 727–57A0145, Revision 2, dated
October 24, 2002, to perform the actions that
are required by this AD, unless the AD
specifies otherwise. The Director of the
Federal Register previously approved the
incorporation by reference of this document
as of December 18, 2002 (67 FR 71808,
December 3, 2002). For copies of the service
information, contact Boeing Commercial
Airplanes, P.O. Box 3707, Seattle,
Washington 98124–2207. For information on
the availability of this material at the
National Archives and Records
Administration (NARA), call (202) 741–6030,
or go to https://www.archives.gov/
federal_register/code_of_federal_regulations/
ibr_locations.html. You may view the AD
docket at the Docket Management Facility,
U.S. Department of Transportation, 400
Seventh Street SW, room PL–401, Nassif
Building, Washington, DC.
Issued in Renton, Washington, on March 2,
2005.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 05–4826 Filed 3–10–05; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2004–19751; Directorate
Identifier 2002–NM–59–AD; Amendment 39–
14001; AD 2005–05–12]
RIN 2120–AA64
Airworthiness Directives; BAE
Systems (Operations) Limited
(Jetstream) Model 4101 Airplanes
by reports of corrosion found on the aft
fuselage frames due to the ingress of
water or liquid. We are issuing this AD
to detect and correct corrosion of the aft
fuselage frames, which could result in
reduced structural integrity of the
fuselage.
DATES: This AD becomes effective April
15, 2005.
The incorporation by reference of
certain publications listed in the AD is
approved by the Director of the Federal
Register as of April 15, 2005.
ADDRESSES: For service information
identified in this AD, contact British
Aerospace Regional Aircraft American
Support, 13850 Mclearen Road,
Herndon, Virginia 20171.
Docket: The AD docket contains the
proposed AD, comments, and any final
disposition. You can examine the 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 U.S. Department of Transportation,
400 Seventh Street SW, room PL–401,
Washington, DC. This docket number is
FAA–2004–19751; the directorate
identifier for this docket is 2002–NM–
59–AD.
FOR FURTHER INFORMATION CONTACT:
Todd Thompson, Aerospace Engineer,
International Branch, ANM–116, FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington
98055–4056; telephone (425) 227–1175;
fax (425) 227–1149.
SUPPLEMENTARY INFORMATION: The FAA
proposed to amend 14 CFR Part 39 with
an AD for all BAE Systems (Operations)
Limited (Jetstream) Model 4101
airplanes. That action, published in the
Federal Register on December 1, 2004
(69 FR 69834), proposed to require
repetitive detailed inspections of the aft
fuselage frames for any discrepancies,
and any applicable corrective actions.
AGENCY:
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the single comment that was
submitted on the proposed AD.
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for all BAE
Systems (Operations) Limited
(Jetstream) Model 4101 airplanes. This
AD requires repetitive detailed
inspections of the aft fuselage frames for
any discrepancies, and any applicable
corrective actions. This AD is prompted
Request To Revise Discussion Section
The commenter requests that we
revise the Discussion section of the
proposed AD. The commenter suggests
that the sentence that describes the area
where corrosion may occur should read,
‘‘This corrosion occurs on frame areas
below floor panel level, between frames
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434 and 555, particularly in the vicinity
of the toilet, galley, and baggage door
due to the ingress of water or liquid.’’
The commenter’s suggestion points out
that, though corrosion particularly
occurs in the vicinity of the toilet,
galley, and baggage door, it may also
occur over a wider area.
We acknowledge that the
commenter’s suggestion is accurate.
However, the Discussion section is not
restated in the final rule. Thus, we have
made no change to the final rule.
Explanation of Change to This AD
We have revised the applicability
statement in paragraph (c) of this AD to
identify model designations as
published in the most recent type
certificate data sheet for the affected
models.
Conclusion
We have carefully reviewed the
available data, including the comment
that was submitted, and determined that
air safety and the public interest require
adopting the AD with the change
described previously. We have
determined that this change will neither
increase the economic burden on any
operator nor increase the scope of the
AD.
Costs of Compliance
This AD will affect about 57 airplanes
of U.S. registry. The required
inspections will take about 30 work
hours per airplane, at an average labor
rate of $65 per work hour. Based on
these figures, the estimated cost of this
AD for U.S. operators is $111,150, or
$1,950 per airplane, per inspection
cycle.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
Section 106, describes the authority of
the FAA Administrator. Subtitle VII,
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in Subtitle VII,
Part A, Subpart III, Section 44701,
‘‘General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
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]]>Agencies
[Federal Register Volume 70, Number 47 (Friday, March 11, 2005)]
[Rules and Regulations]
[Pages 12120-12124]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-4826]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2004-19530; Directorate Identifier 2002-NM-274-AD;
Amendment 39-14008; AD 2005-05-19]
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 superseding an existing airworthiness directive
(AD), which applies to certain Boeing Model 727 airplanes. That AD
currently requires repetitive detailed inspections to detect cracking,
corrosion, and existing stop-drilled repairs of cracking in the upper
chord of the rear spar of the wing; and repair if necessary. This new
AD requires new repetitive inspections to detect cracks, corrosion,
minor surface defects, and existing stop-drilled repairs of cracks in
the upper and lower chords of the front and rear spars of the wing; and
repair if necessary. This AD is prompted by our determination that
further rulemaking action is necessary to require additional actions
specified in the referenced service bulletin. We are issuing this AD to
prevent structural failure of the wing and fuel leaks in the airplane
due to stress corrosion cracking of the wing spar chords.
DATES: This AD becomes effective April 15, 2005.
On December 18, 2002 (67 FR 71808, December 3, 2002), the Director
of the Federal Register approved the incorporation by reference of
Boeing Alert Service Bulletin 727-57A0145, Revision 2, dated October
24, 2002.
ADDRESSES: For service information identified in this AD, contact
Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-
2207.
Docket: The AD docket contains the proposed AD, comments, and any
final disposition. You can examine the 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 U.S.
Department of Transportation, 400 Seventh Street SW, room PL-401,
Washington, DC. This docket number is FAA-2004-19530; the directorate
identifier for this docket is 2002-NM-274-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: The FAA proposed to amend part 39 of the
Federal Aviation Regulations (14 CFR Part 39) with an AD to supersede
AD 2002-24-05, amendment 39-12970 (67 FR 71808, December 3, 2002). The
existing AD applies to certain Boeing Model 727 airplanes. The proposed
AD was published in the Federal Register on November 5, 2004 (69 FR
64506), to require new repetitive inspections to detect cracks,
corrosion, minor surface defects, and existing stop-drilled repairs of
cracks in the upper and lower chords of the front and rear spars of the
wing; and repair if necessary.
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the comment that has been
submitted on the proposed AD. The commenter supports the proposed AD.
Explanation of Change to Model Designation
We have revised the subject heading of the existing AD to identify
model designations as published in the most recent type certificate
data sheet for the affected models.
Changes to Delegation Authority
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).
Conclusion
We have carefully reviewed the available data, including the
comment that has been submitted, and determined that air safety and the
public interest require adopting the AD with the change described
previously. We have determined that this change will neither increase
the economic burden on any operator nor increase the scope of the AD.
Costs of Compliance
There are about 1,426 airplanes of the affected design in the
worldwide fleet. This AD will affect about 946 airplanes of U.S.
registry.
For Group 1 airplanes identified in the service bulletin, the
actions (Part 1 of the Accomplishment Instructions of the service
bulletin) that are required by AD 2002-24-05 and retained in this AD
take about 8 work hours per airplane, at an average labor rate of $65
per work hour. Based on these figures, the estimated cost of the
currently required actions is $520 per airplane.
The following table provides the estimated costs for U.S. operators
to comply with the new actions required by this AD. The average labor
rate is $65 per work hour.
[[Page 12121]]
Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Per airplane
cost, per
For airplanes identified in the service bulletin as-- Actions in-- Work hours-- inspection
cycle--
--------------------------------------------------------------------------------------------------------------------------------------------------------
Group 1.............................................................................. Part 2 of the Accomplishment 30 $1,950
Instructions of the service
bulletin.
Group 1.............................................................................. Part 3 of the Accomplishment 21 1,365
Instructions of the service
bulletin.
Group 1.............................................................................. Part 4 of the Accomplishment 68 4,420
Instructions of the service
bulletin.
Group 1.............................................................................. Part 8 of the Accomplishment 8 520
Instructions of the service
bulletin.
Group 1.............................................................................. Part 9 of the Accomplishment 30 1,950
Instructions of the service
bulletin.
Group 2.............................................................................. Part 5 of the Accomplishment 52 3,380
Instructions of the service
bulletin.
Group 2.............................................................................. Part 6 of the Accomplishment 110 7,150
Instructions of the service
bulletin.
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Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory 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. 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 FAA amends Sec. 39.13 by removing amendment 39-12970 (67 FR
71808, December 3, 2002), and by adding the following new airworthiness
directive (AD):
2005-05-19 Boeing: Amendment 39-14008. Docket No. FAA-2004-19530;
Directorate Identifier 2002-NM-274-AD.
Effective Date
(a) This AD becomes effective April 15, 2005.
Affected ADs
(b) This AD supersedes AD 2002-24-05, amendment 39-12970.
Applicability
(c) This AD applies to Boeing Model 727, 727C, 727-100, -100C, -
200, and -200F series airplanes, line numbers 1 through 1832
inclusive; certificated in any category.
Unsafe Condition
(d) This AD was prompted by our determination that further
rulemaking action is necessary to require additional actions
specified in the referenced service bulletin. We are issuing this AD
to prevent structural failure of the wing and fuel leaks in the
airplane due to stress corrosion cracking of the wing spar chords.
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 References
(f) The term ``the service bulletin,'' as used in this AD, means
Boeing Alert Service Bulletin 727-57A0145, Revision 2, dated October
24, 2002.
Inspection Requirements of AD 2002-24-05, Amendment 39-12970
Inspection
(g) For airplanes specified as ``Group 1'' airplanes in the
service bulletin: Within 20 years after the date of manufacture or
within 90 days after December 18, 2002 (the effective date of AD
2002-24-05, amendment 39-12970), whichever occurs later, perform an
external detailed inspection for cracking, corrosion, and existing
stop-drilled repairs of cracking in the upper chord on the rear spar
from Wing Butt Line (WBL) 70.5 through WBL 249.3, per the service
bulletin, paragraph 3.B, ``Work Instructions,'' Part 1. Thereafter,
repeat the inspection at intervals not to exceed 2 years.
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
mirrors, magnifying lenses, etc., may be necessary. Surface cleaning
and elaborate procedures may be required.''
[[Page 12122]]
New Actions Required by This AD
Inspections Specified in Parts 2 Through 6, and 8 and 9 of the
Service Bulletin
(h) Accomplish the applicable inspection(s) specified in
paragraphs (h)(1) through (h)(7) of this AD at the later of the
applicable times specified in the ``Threshold'' and ``Grace Period''
columns in Table 1 of this AD, and repeat the inspection(s) at the
time specified in the ``Repetitive Interval'' column of Table 1 of
this AD. Accomplishment of the inspection required by paragraph
(h)(1) of this AD terminates the repetitive inspection requirements
of paragraph (g) of this AD.
Table 1.--Compliance Times for Inspections Specified in Parts 2 Through 6, and 8 and 9 of Service Bulletin
----------------------------------------------------------------------------------------------------------------
For airplanes identified in the Repetitive
service bulletin as-- Threshold-- Grace period-- interval-- Do--
----------------------------------------------------------------------------------------------------------------
(1) Group 1..................... Before 20 years Within 1 year None.............. A high frequency
since the date of after the eddy current
issuance of the effective date of (HFEC) inspection
original this AD. and detailed
Airworthiness inspection of the
Certificate or upper chord the
the date of rear spar from
issuance of the WBL 70.5 to the
original Export wing tip for
Certificate of cracks,
Airworthiness. corrosion, minor
surface defects,
and existing stop-
drilled repairs
of cracking, in
accordance with
paragraph 3.B.,
Work
Instructions,
Part 2, of the
Accomplishment
Instructions of
the service
bulletin.
(2) Group 1..................... Before 20 years Within 2 years At intervals not A detailed
since the date of after the to exceed 2 years. inspection of the
issuance of the effective date of upper and lower
original this AD. chord of the
Airworthiness front spar and
Certificate or the lower chord
the date of of the rear spar
issuance of the from WBL 70.5 to
Original Export the wing tip for
Certificate of cracks,
Airworthiness. corrosion, minor
surface defects,
and existing stop-
drilled repairs
of cracking
(initial
inspection only),
in accordance
with paragraph
3.B., Work
Instructions,
Part 3, of the
Accomplishment
Instructions of
the service
bulletin.
(3) Group 1..................... Before 20 years Within 4 years At intervals not An HFEC inspection
since the date of after the to exceed 4 years. of the upper and
issuance of the effective date of lower chords of
original this AD. the rear spar
Airworthiness from WBL 70.5 to
Certificate or the wing tip for
the date of cracks,
issuance of the corrosion, minor
original Export surface defects,
Certificate of and existing stop-
Airworthiness. drilled repairs
of cracking
(initial
inspection only),
in accordance
with paragraph
3.B., Work
Instructions,
Part 4, of the
Accomplishment
Instructions of
the service
bulletin.
(4) Group 1..................... Within 2 years None.............. At intervals not A detailed
after doing the to exceed 2 years. inspection of the
actions required upper chord of
by paragraph the rear spar WBL
(h)(1) of this AD. 70.5 to the wing
tip for cracks,
corrosion, minor
surface defects,
and existing stop-
drilled repairs
of cracking
(initial
inspection only),
in accordance
with paragraph
3.B., Work
Instructions,
Part 8, of the
Accomplishment
Instructions of
the service
bulletin.
[[Page 12123]]
(5) Group 1..................... Within 4 years None.............. At intervals not An HFEC inspection
after doing the to exceed 4 years. of doing the not
actions required to the upper
by paragraph chord actions
(h)(1) of this AD. exceed 4 of the
rear spar
required by years
from WBL 70.5 to
paragraph the
wing tip for
(h)(1) of cracks,
this AD
corrosion, minor
surface defects,
and existing stop-
drilled repairs
of cracking
(initial
inspection only),
in accordance
with paragraph
3.B., Work
Instructions,
Part 9, of the
Accomplishment
Instructions of
the service
bulletin.
(6) Group 2..................... Before 20 years Within 2 years At intervals not An exterior
since the date of after the to exceed 2 years. detailed
issuance of the effective date of inspection of the
original this AD. upper and lower
Airworthiness chords of the
Certificate or front and rear
the date of spars from WBL
issuance of the 70.5 to the wing
original Export tip for cracks,
Certificate of corrosion, minor
Airworthiness. surface defects,
and existing stop-
drilled repairs
of cracking
(initial
inspection only),
in accordance
with paragraph
3.B., Work
Instructions,
Part 5, of the
Accomplishment
Instructions of
the service
bulletin.
(7) Group 2..................... Before 20 years Within 4 years At intervals not An HFEC inspection
since the date of after the to exceed 4 years. of the upper and
issuance of the effective date of lower chords of
original this AD. the front and
Airworthiness rear spars from
Certificate or WBL 70.5 to the
the date of wing tip for
issuance of the cracks,
original Export corrosion, minor
Certificate of surface defects,
Airworthiness. and existing stop-
drilled repairs
of cracking
(initial
inspection only),
in accordance
with paragraph
3.B., Work
Instructions,
Part 6, of the
Accomplishment
Instructions of
the service
bulletin.
----------------------------------------------------------------------------------------------------------------
Corrective Actions
(i) If any crack, corrosion, or minor surface defect is detected
during any inspection required by this AD, before further flight, do
the applicable corrective actions in accordance with Part 7 of the
Accomplishment Instructions of the service bulletin, except as
provided by paragraph (j) of this AD.
(j) If any crack or corrosion is detected during any inspection
required by this AD that exceeds the limits specified in the service
bulletin, and the bulletin specifies to contact Boeing for
appropriate action: Before further flight, repair in accordance with
a method approved by the Manager, Seattle Aircraft Certification
Office (ACO), FAA; or in accordance with data meeting the
certification basis of the airplane approved by an Authorized
Representative for the Boeing Delegation Option Authorization
Organization who has been authorized by the Manager, Seattle ACO, to
make such findings. For a repair method to be approved, the approval
must specifically reference this AD.
(k) If any existing stop-drilled repair of previous cracking is
detected during any inspection required by this AD, before further
flight, permanently repair crack in accordance with paragraph 3.B.,
Work Instructions, Part 7, paragraph 2., ``Crack Repair'' of the
Accomplishment Instructions of the service bulletin.
(l) Before further flight following any inspection or repair
required by this AD, apply a wet layer of BMS 3-23 organic corrosion
inhibiting compound or Boeing equivalent, in accordance with the
Accomplishment Instructions of the service bulletin.
Alternative Methods of Compliance (AMOCs)
(m)(1) The Manager, Seattle ACO, FAA, has the authority to
approve AMOCs for this AD, if requested using the procedures found
in 14 CFR 39.19.
(2) Alternative methods of compliance, approved previously in
accordance with AD 2002-24-05, amendment 39-12970, are
[[Page 12124]]
approved as alternative methods of compliance with 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 Delegation Option
Authorization Organization who has been authorized by the Manager,
Seattle ACO, to make such findings. For a repair method to be
approved, the approval must specifically reference this AD.
Material Incorporated by Reference
(n) You must use Boeing Alert Service Bulletin 727-57A0145,
Revision 2, dated October 24, 2002, to perform the actions that are
required by this AD, unless the AD specifies otherwise. The Director
of the Federal Register previously approved the incorporation by
reference of this document as of December 18, 2002 (67 FR 71808,
December 3, 2002). For copies of the service information, contact
Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington
98124-2207. For information on the availability of this material at
the National Archives and Records Administration (NARA), call (202)
741-6030, or go to https://www.archives.gov/federal_register/code_
of_federal_regulations/ibr_locations.html. You may view the AD
docket at the Docket Management Facility, U.S. Department of
Transportation, 400 Seventh Street SW, room PL-401, Nassif Building,
Washington, DC.
Issued in Renton, Washington, on March 2, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-4826 Filed 3-10-05; 8:45 am]
BILLING CODE 4910-13-P
