[Federal Register: November 23, 2007 (Volume 72, Number 225)]
[Proposed Rules]
[Page 65678-65681]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr23no07-15]
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Proposed Rules
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains notices to the public of
the proposed issuance of rules and regulations. The purpose of these
notices is to give interested persons an opportunity to participate in
the rule making prior to the adoption of the final rules.
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[[Page 65678]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-0223; Directorate Identifier 2007-NM-156-AD]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 727 Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: The FAA proposes to supersede an existing airworthiness
directive (AD) that applies to certain Boeing Model 727 series
airplanes. The existing AD currently requires repetitive inspections to
detect cracks and loose brackets of the elevator rear spar, and
corrective actions if necessary. The existing AD also provides for an
optional terminating action for the repetitive inspections. This
proposed AD would reduce the repetitive intervals of the inspections,
mandate the previously optional terminating action for the repetitive
inspections, and no longer allow stop-drilling. This proposed AD
results from new reports of cracks, elongated fastener holes, and loose
fittings of the elevator rear spar. We are proposing this AD to prevent
cracking of the elevator rear spar at the tab hinge locations, which
could cause excessive freeplay of the elevator control tab and possible
tab flutter, and consequent loss of control of the airplane.
DATES: We must receive comments on this proposed AD by January 7, 2008.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to http://www.regulations.gov.
Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
For service information identified in this AD, contact Boeing
Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-2207.
Examining the AD Docket
You may examine the AD docket on the Internet at http://www.regulations.gov
; or in person at the Docket Management Facility
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this proposed AD, the regulatory
evaluation, any comments received, and other information. The street
address for the Docket Office (telephone 800-647-5527) is in the
ADDRESSES section. Comments will be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION CONTACT: Berhane Alazar, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
917-6577; fax (425) 917-6590.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2007-0223;
Directorate Identifier 2007-NM-156-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD because of those comments.
We will post all comments we receive, without change, to http://www.regulations.gov
, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
On March 12, 1996, we issued AD 96-06-05, amendment 39-9542 (61 FR
11529, March 21, 1996), for certain Boeing Model 727 series airplanes.
That AD requires repetitive inspections to detect cracks and loose
brackets of the elevator rear spar and repair if necessary, and
provides an optional terminating modification for the inspections. That
AD was prompted by reports of cracking in the spar radii at the tab
hinge location of the elevator rear spar. We issued that AD to prevent
cracking in elements of the elevator rear spar assembly, which could
result in excessive freeplay of the elevator control tab and possible
tab flutter.
Actions Since Existing AD Was Issued
Since we issued AD 96-06-05, we have received reports of additional
cracks, elongated fastener holes, and loose fittings on airplanes on
which the repetitive detailed inspections required by that AD have been
initiated. We have determined that the existing long-term repetitive
detailed inspections do not provide an acceptable level of safety. This
determination, along with a better understanding of the human factors
associated with numerous continual inspections, has led us to consider
placing less emphasis on inspections and more emphasis on design
improvements. Therefore, we have determined that it is necessary to
reduce the repetitive intervals of certain inspections and to require
replacement of the elevator rear spar with a new elevator rear spar and
new support fittings to adequately address the identified unsafe
condition of this proposed AD.
In addition, we have determined that the stop-drilling required by
AD 96-06-05 does not provide an adequate level of safety. Therefore, in
this proposed AD, stop-drilling of cracks of the elevator rear spar
assembly is no longer considered to be an acceptable method of repair.
Relevant Service Information
We have reviewed Boeing Service Bulletin 727-55-0089, Revision 1,
dated March 2, 2000. (We referred to the original release of the
service bulletin in AD 96-06-05 as the appropriate source of service
information for the required actions.) The repetitive detailed
inspections, stop-drill if necessary, and
[[Page 65679]]
optional terminating action (i.e., replacement of the elevator rear
spar with a new elevator rear spar and support fittings) are identical
to those actions specified in the original service bulletin. Revision 1
changes the part accountability paragraph and the list of airplane
operators. No more work is necessary on airplanes changed per the
original release of the service information, if the optional
terminating action was done. Accomplishing the actions specified in the
service information is intended to adequately address the unsafe
condition.
FAA's Determination and Requirements of the Proposed AD
We have evaluated all pertinent information and identified an
unsafe condition that is likely to develop on other airplanes of the
same type design. For this reason, we are proposing this AD, which
would supersede AD 96-06-05 and would retain the requirements of the
existing AD. This proposed AD would also require accomplishing the
actions specified in service information described previously, except
as discussed under ``Differences Between the Proposed AD and Service
Information.''
Differences Between the Proposed AD and Service Information
Paragraph 1.A, ``Effectivity,'' of Boeing Service Bulletin 727-55-
0089, Revision 1, contains an error in that it identifies only Model
727-100 and -200 series airplanes as the affected airplanes. Although
Model 727, 727C, 727-100C, and 727-200F series airplanes were
inadvertently omitted from that paragraph, those airplanes were
identified by variable numbers in the effectivity listing. Therefore,
the applicability of this proposed AD would affect Model 727, 727C,
727-100, 727-100C, 727-200, and 727-200F series airplanes.
As discussed previously, this proposed AD would require replacement
of the elevator rear spar with a new elevator rear spar and support
fittings, which would terminate the repetitive inspection requirements.
The service information provides the terminating action as an option.
Where the service information describes stop-drilling as an interim
method of repair, this proposed AD would not permit stop-drilling as an
interim method of repair. As discussed previously, we have determined
that, for the purposes of this proposed AD, stop-drilling does not
provide an adequate level of safety.
Additionally, the service information recommends that certain
repetitive inspection intervals be done within 1,600 flight hours or
within 18 months, whichever occurs first. This proposed AD would
require a repetitive interval not to exceed 1,600 flight hours for
those inspections. Calendar time (i.e., ``18 months'') is not
appropriate for addressing problems associated with fatigue such as the
cracking addressed by this proposed AD. The determination that calendar
time is not appropriate for addressing problems associated with fatigue
also was addressed in the preamble of AD 96-06-05.
We have coordinated these differences with Boeing.
Change to Existing AD
This proposed AD would retain all requirements of AD 96-06-05.
Since AD 96-06-05 was issued, the AD format has been revised, and
certain paragraphs have been rearranged. As a result, the corresponding
paragraph identifiers have changed in this proposed AD, as listed in
the following table:
Revised Paragraph Identifiers
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Corresponding requirement
Requirement in AD 96-06-05 in this proposed AD
------------------------------------------------------------------------
paragraph (a)............................. paragraph (f).
paragraph (b)............................. paragraph (g).
paragraph (c)............................. paragraph (h).
paragraph (d)............................. paragraph (i).
paragraph (e)............................. paragraph (j).
paragraph (f)............................. paragraph (k).
paragraph (g)............................. paragraph (l).
------------------------------------------------------------------------
We have revised the applicability of the existing AD to identify
model designations as published in the most recent type certificate
data sheet for the affected models. In addition, we have revised the
applicability of the existing AD to refer to the latest service
bulletin (i.e., Boeing Service Bulletin 727-55-0089, Revision 1), and
refer to affected models not identified in the referenced service
bulletin, as discussed previously.
We have changed all references to a ``visual inspection'' in AD 96-
06-05 to ``detailed inspection'' in this proposed AD. We also added a
new note defining that inspection and renumbered subsequent notes.
Costs of Compliance
There are about 815 airplanes of the affected design in the
worldwide fleet. The following table provides the estimated costs for
U.S. operators to comply with this proposed AD.
Estimated Costs
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Number of U.S.-
Action Work hours Average labor Parts Cost per airplane registered Fleet cost
rate per hour airplanes
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Detailed Inspection (required by AD 17 $80 None................. $1,360, per 448 $609,280, per
96-06-05). inspection cycle. inspection cycle.
Terminating action (new proposed 416 80 $14,975.............. $48,255.............. 448 $21,618,240.
action).
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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 proposed AD would not have federalism
implications under Executive Order
[[Page 65680]]
13132. This proposed AD would 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 the proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the 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 proposed AD and placed it in the AD docket. See the
ADDRESSES section for a location to examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
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]
2. The Federal Aviation Administration (FAA) amends Sec. 39.13 by
removing amendment 39-9542 (61 FR 11529, March 21, 1996) and adding the
following new airworthiness directive (AD):
Boeing: Docket No. FAA-2007-0223; Directorate Identifier 2007-NM-
156-AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by January
7, 2008.
Affected ADs
(b) This AD supersedes AD 96-06-05.
Applicability
(c) This AD applies to Boeing Model 727, 727C, 727-100, 727-
100C, 727-200, and 727-200F series airplanes, certificated in any
category, as identified in Boeing Service Bulletin 727-55-0089,
Revision 1, dated March 2, 2000.
Unsafe Condition
(d) This AD results from new reports of cracks, elongated
fastener holes, and loose fittings of the elevator rear spar. We are
issuing this AD to prevent cracking of the elevator rear spar at the
tab hinge locations, which could cause excessive freeplay of the
elevator control tab and possible tab flutter, and consequent loss
of control of the airplane.
Compliance
(e) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Requirements of AD 96-06-05
Repetitive Inspections and Follow-On Actions
(f) For airplanes on which the modification or repair described
in Boeing Service Bulletin 727-55-0085, dated August 31, 1984
(specified as terminating action in AD 84-22-02, amendment 39-4951),
has not been accomplished and the repetitive inspections required by
AD 84-22-02 have not been initiated: Prior to the accumulation of
8,000 total flight hours since date of manufacture, or within 300
flight hours after April 22, 1996 (the effective date of AD 96-06-
05), whichever occurs later, perform a detailed inspection to detect
cracks and loose hinge brackets of the elevator rear spar in the
area along the upper and lower edges at the shear plate, in
accordance with Boeing Service Bulletin 727-55-0089, dated June 29,
1995. Then accomplish the follow-on actions (i.e., repetitive
inspections, stop-drilling, modification) in accordance with that
service bulletin, at the times specified as follows:
Note 1: For the purposes of this AD, a detailed inspection is:
``An intensive examination of a specific item, installation, or
assembly to detect damage, failure, or irregularity. Available
lighting is normally supplemented with a direct source of good
lighting at an intensity deemed appropriate. Inspection aids such as
mirror, magnifying lenses, etc., may be necessary. Surface cleaning
and elaborate procedures may be required.''
Note 2: AD 84-22-02 pertains to the one-piece elevator rear
spar.
(1) Repeat the detailed inspection thereafter at intervals not
to exceed 1,600 flight hours.
(2) If any crack is detected and stop-drilled as a result of any
inspection required by this paragraph, accomplish the requirements
of paragraph (l) of this AD, except as provided by paragraph (o) of
this AD, at the times specified in paragraph (l) of this AD.
Repetitive Inspections and Follow-On Actions
(g) For airplanes on which the modification or repair described
in Boeing Service Bulletin 727-55-0085, dated August 31, 1984
(specified as terminating action in AD 84-22-02), has not been
accomplished and the repetitive inspections required by AD 84-22-02
have been initiated: Accomplish either paragraph (g)(1) or (g)(2) of
this AD, as applicable.
(1) If no crack has been detected as a result of inspections
required by AD 84-22-02: Within 1,600 flight hours after the last
inspection required by that AD, perform a detailed inspection to
detect cracks and loose brackets of the elevator rear spar in the
area along the upper and lower edges at the shear plate, in
accordance with the Boeing Service Bulletin 727-55-0089, dated June
29, 1995. Accomplish follow-on actions (i.e., repetitive inspection,
stop-drilling, modification) in accordance with that service
bulletin, except as provided by paragraph (o) of this AD, at the
times specified as follows:
(i) Repeat the detailed inspection thereafter at intervals not
to exceed 1,600 flight hours.
(ii) If any crack is detected and stop-drilled as a result of
any inspection required by this paragraph, accomplish the
requirements of paragraph (l) of this AD, except as provided by
paragraph (o) of this AD, at the times specified in paragraph (l) of
this AD.
(2) If any crack has been stop-drilled in accordance with AD 84-
22-02, accomplish the requirements of paragraph (l) of this AD,
except as provided by paragraph (o) of this AD, at the times
specified in paragraph (l) of this AD.
(h) For airplanes on which the modification or repair described
in Boeing Service Bulletin 727-55-0085, dated August 31, 1984
(specified as terminating action in AD 84-22-02, amendment 39-4951),
has been accomplished: Within 4,000 flight hours after April 22,
1996, perform a detailed inspection to detect cracks and loose hinge
brackets of the elevator rear spar in the area along the upper and
lower edges at the shear plate, in accordance with Boeing Service
Bulletin 727-55-0089, dated June 29, 1995. Accomplish follow-on
actions (i.e., repetitive inspections, stop-drilling, modification)
in accordance with that service bulletin, except as provided by
paragraph (o) of this AD, at the times specified as follows:
(1) Repeat the detailed inspection thereafter at intervals not
to exceed 4,000 flight hours, except as provided by paragraph (n) of
this AD.
(2) If any crack is detected and stop-drilled as a result of any
inspection required by this paragraph, accomplish the requirements
of paragraph (l) of this AD, except as provided by paragraph (o) of
this AD, at the times specified in paragraph (l) of this AD.
(i) For airplanes on which the modification or repair described
in Boeing Service Bulletin 727-55-087, dated June 20, 1986
(specified as terminating action in AD 87-24-03, amendment 39-5769),
has not been accomplished and the repetitive inspections required by
AD 87-24-03 have not been initiated: Accomplish the requirements of
paragraph (i)(1) of this AD at the earliest of the times specified
in paragraph (i)(2) of this AD.
Note 3: AD 87-24-03 pertains to the two-piece elevator rear
spar.
(1) Perform a detailed inspection to detect cracks and loose
hinge brackets of the elevator rear spar in the area along the upper
and lower edges at the shear plate, at the earliest of the times
specified in paragraph (i)(2) of this AD, and in accordance with
Boeing Service Bulletin 727-55-0089, dated June 29, 1995. Accomplish
follow-on actions (i.e., repetitive inspection, stop-drilling,
modification) in accordance with that service bulletin, at the times
specified as follows:
[[Page 65681]]
(i) Repeat the detailed inspection thereafter at intervals not
to exceed 4,000 flight hours, except as provided by paragraph (n) of
this AD.
(ii) If any crack is detected and stop-drilled as a result of
any inspection required by this paragraph, accomplish the
requirements of paragraph (l) of this AD, except as provided by
paragraph (o) of this AD, at the times specified in paragraph (l) of
this AD.
(2) Accomplish the initial detailed inspection required by
paragraph (i)(1) of this AD at the earliest of the following times:
(i) Prior to the accumulation of 27,000 total flight hours since
date of manufacture, or within 4,000 flight hours after December 24,
1987 (the effective date of AD 87-24-03), whichever occurs later; or
(ii) Prior to the accumulation of 12,000 total flight hours
since date of manufacture, or within 4,000 flight hours after April
22, 1996, whichever occurs later; or
(iii) Prior to the accumulation of 27,300 total flight hours
since date of manufacture, or within 300 flight hours after April
22, 1996, whichever occurs later.
(j) For airplanes on which the modification or repair described
in Boeing Service Bulletin 727-55-087, dated June 20, 1986
(specified as terminating action in AD 87-24-03), has not been
accomplished and the repetitive inspections required by AD 87-24-03
have been initiated: Accomplish either paragraph (j)(1) or (j)(2) of
this AD, as applicable.
(1) If no crack has been detected as a result of inspections
required by AD 87-24-03: Within 4,000 flight hours after the last
inspection required by that AD, perform a detailed inspection to
detect cracks and loose brackets of the elevator rear spar in the
area along the upper and lower edges at the shear plate, in
accordance with Boeing Service Bulletin 727-55-0089, dated June 29,
1995, except as provided by paragraph (m) of this AD. Accomplish
follow-on actions (i.e., repetitive inspection, stop-drilling,
modification) in accordance with that service bulletin, except as
provided by paragraph (o) of this AD, at the times specified as
follows:
(i) Repeat the detailed inspection thereafter at intervals not
to exceed 4,000 flight hours, except as provided by paragraph (n) of
this AD.
(ii) If any crack is detected and stop-drilled as a result of
any inspection required by paragraph (j)(1) of this AD, accomplish
the requirements of paragraph (l) of this AD, except as provided by
paragraph (o) of this AD, at the times specified in paragraph (l) of
this AD.
(2) If any crack has been detected and stop-drilled in
accordance with AD 87-24-03, accomplish the requirements of
paragraph (l) of this AD, except as provided by paragraph (o) of
this AD, at the times specified in paragraph (l) of this AD.
(k) For airplanes on which the modification or repair described
in Boeing Service Bulletin 727-55-087, dated June 20, 1986
(specified as terminating action in AD 87-24-03), has been
accomplished: Within 4,000 flight hours after April 22, 1996,
perform a detailed inspection to detect cracks and loose hinge
brackets of the elevator rear spar in the area along the upper and
lower edges at the shear plate, in accordance with Boeing Service
Bulletin 727-55-0089, dated June 29, 1995. Accomplish follow-on
actions (i.e., repetitive inspection, stop-drilling, modification)
in accordance with the service bulletin, except as provided by
paragraph (o) of this AD, at the times specified as follows:
(1) Repeat the detailed inspection thereafter at intervals not
to exceed 4,000 flight hours, except as provided by paragraph (n) of
this AD.
(2) If any crack is detected and stop-drilled as a result of any
inspection required by this paragraph, accomplish the requirements
of paragraph (l) of this AD, except as provided by paragraph (o) of
this AD, at the times specified in that paragraph.
(l) If any crack is detected and stop-drilled in accordance with
paragraph (f)(2), (g)(1)(ii), (g)(2), (h)(2), (i)(1)(ii),
(j)(1)(ii), (j)(2), or (k)(2) of this AD, accomplish the following,
except as provided by paragraphs (o) and (p) of this AD:
(1) Within 1,600 flight hours after stop-drilling, perform a
detailed inspection to detect cracks and loose hinge brackets of the
elevator rear spar in the area along the upper and lower edges at
the shear plate, and accomplish follow-on actions (i.e., stop-
drilling, modification) in accordance with the service bulletin. If
any crack growth is detected after stop-drilling, prior to further
flight, modify the elevator rear spar in accordance with Part II of
the Accomplishment Instructions of Boeing Service Bulletin 727-55-
0089, dated June 29, 1995. Accomplishment of this modification
constitutes terminating action for the repetitive inspection
requirements of this AD.
(2) Within 3,200 flight hours after stop-drilling, modify the
elevator rear spar in accordance with Part II of the Accomplishment
Instructions of Boeing Service Bulletin 727-55-0089, dated June 29,
1995. Accomplishment of this modification constitutes terminating
action for the repetitive inspection requirements of this AD.
New Actions Required by This AD
New Service Information
(m) As of the effective date of this AD, use only the
Accomplishment Instructions of Boeing Service Bulletin 727-55-0089,
Revision 1, dated March 2, 2000, to do the repetitive detailed
inspections required by this AD.
Certain Repetitive Inspections at Reduced Intervals
(n) For airplanes being inspected at intervals not to exceed
4,000 flight hours in accordance with paragraphs (h)(1), (i)(1)(i),
(j)(1)(i), and (k)(1) of this AD: As of the effective date of this
AD, do those inspections within 1,600 flight hours since the last
detailed inspection or 6 months after the effective date of this AD,
whichever occurs later, and thereafter at intervals not to exceed
1,600 flight hours.
Stop-Drilling Prohibited
(o) As of the effective date of this AD, stop-drilling required
by paragraphs (f) through (l) inclusive of this AD is prohibited.
Replacement of Cracked Rear Spars/Loose Brackets
(p) As of the effective date of this AD, if any cracked rear
spar or loose bracket is detected during any inspection required by
this AD, before further flight, do the replacement specified in
paragraph (q) of this AD.
Terminating Replacement
(q) Within 18 months after the effective date of this AD,
replace the elevator rear spar with a new elevator rear spar and
support fittings, in accordance with Part II of the Accomplishment
Instructions of Boeing Service Bulletin 727-55-0089, Revision 1,
dated March 2, 2000. Accomplishing the replacement constitutes
terminating action for the requirements of this AD.
(r) Accomplishing the replacement before the effective date of
this AD in accordance with Boeing Service Bulletin 727-55-0089,
dated June 29, 1995, is considered acceptable for compliance with
the corresponding action specified in paragraph (q) of this AD.
Alternative Methods of Compliance (AMOCs)
(s)(1) The Manager, Seattle Aircraft Certification Office (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) To request a different method of compliance or a different
compliance time for this AD, follow the procedures in 14 CFR 39.19.
Before using any approved AMOC on any airplane to which the AMOC
applies, notify your appropriate principal inspector (PI) in the FAA
Flight Standards District Office (FSDO), or lacking a PI, your local
FSDO.
(3) An AMOC that provides an acceptable level of safety may be
used for any repair required by this AD, if it is approved by an
Authorized Representative for the Boeing Commercial Airplanes
Delegation Option Authorization Organization who has been authorized
by the Manager, Seattle ACO, to make those findings. For a repair
method to be approved, the repair must meet the certification basis
of the airplane, and the approval must specifically refer to this
AD.
(4) AMOCs approved previously in accordance with AD 96-06-05 are
approved as AMOCs for the corresponding provisions of this AD.
Issued in Renton, Washington, on November 7, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E7-22814 Filed 11-21-07; 8:45 am]
BILLING CODE 4910-13-P