Airworthiness Directives; Boeing Model 727 Series Airplanes, 36064-36067 [05-12297]
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Federal Register / Vol. 70, No. 119 / Wednesday, June 22, 2005 / Proposed Rules
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–21593; Directorate
Identifier 2002–NM–328–AD]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 727 Series Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: The FAA proposes to
supersede an existing airworthiness
directive (AD) for certain Boeing Model
727 series airplanes. That AD currently
requires repetitive visual inspections for
cracking of the forward entry doorway
forward frame and repair if necessary.
That AD also provides an optional
modification that constitutes
terminating action. This proposed AD
would require adding new post-repair
and post-modification inspections for
previously repaired or modified
airplanes, mandating the optional
modification, and adding airplanes to
the applicability of the AD. This
proposed AD is prompted by reports of
cracking of the forward entry doorway
forward frame of airplanes previously
modified. We are proposing this AD to
prevent the loss of the structural
integrity of the forward entry doorway
due to cracking of the frame at BS 303.9,
and consequent cracking of the fuselage
skin and rapid decompression of the
airplane.
DATES: We must receive comments on
this proposed AD by August 8, 2005.
ADDRESSES: Use one of the following
addresses to submit comments on this
proposed 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.
For service information identified in
this proposed AD, contact Boeing
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Commercial Airplanes, P.O. Box 3707,
Seattle, Washington 98124–2207.
You can examine the contents of this
AD docket on the Internet at https://
dms.dot.gov, or at the Docket
Management Facility, U.S. Department
of Transportation, 400 Seventh Street
SW., room PL–401, on the plaza level of
the Nassif Building, Washington, DC.
This docket number is FAA–2005–
21593; the directorate identifier for this
docket is 2002–NM–328–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:
Comments Invited
We invite you to submit any written
relevant data, views, or arguments
regarding this proposed AD. Send your
comments to an address listed under
ADDRESSES. Include ‘‘Docket No. FAA–
2005–21593; Directorate Identifier
2002–NM–328–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of the proposed AD. We will
consider all comments received by the
closing date and may amend the
proposed AD in light of those
comments.
We will post all comments we
receive, without change, to https://
dms.dot.gov, including any personal
information you provide. We will also
post a report summarizing each
substantive verbal contact with FAA
personnel concerning this proposed AD.
Using the search function of our docket
web site, anyone can find and read the
comments in any of our dockets,
including the name of the individual
who sent the comment (or signed the
comment on behalf of an association,
business, labor union, etc.). You can
review the DOT’s complete Privacy Act
Statement in the Federal Register
published on April 11, 2000 (65 FR
19477–78), or you can visit https://
dms.dot.gov.
Examining the Docket
You can examine the AD docket 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 DOT
street address stated in the ADDRESSES
section. Comments will be available in
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the AD docket shortly after the DMS
receives them.
Discussion
On April 11, 1991, we issued AD 91–
09–07, amendment 39–6982 (56 FR
18687, April 24, 1991), applicable to
certain Boeing Model 727 series
airplanes. That AD requires repetitive
visual inspections for cracking of the
forward entry doorway forward frame
and repair if necessary. That AD also
provides an optional modification that
constitutes terminating action. That
action was prompted by reports of
cracking of the forward entry doorway
forward frame of airplanes previously
modified. We issued that AD to prevent
loss of the structural integrity of the
forward entry doorway.
Actions Since Existing AD Was Issued
Since we issued AD 91–09–07, we
have received several reports indicating
cracking found on certain frames of
certain Boeing Model 727 series
airplanes. The cracks were found on
airplanes that had accomplished the
optional terminating action specified in
AD 91–09–07. Those airplanes had
between 32,000 and 35,000 total flight
cycles, and ranged between 0.25 inch
and 0.50 inch long. The cracks initiated
from the web cut-outs at stringer S–16L
at Body Station (BS) 303.9, and were
typically found during routine
maintenance. Additionally, cracking
was also reported on certain Model 727
series airplanes that were not included
in the applicability of AD 91–09–07.
The cracking is primarily attributed to
cyclic fatigue loading at the frame web
cut-outs. Cracking of the frames, if not
corrected, could result in loss of the
structural integrity of the forward entry
doorway forward frame, and consequent
cracking of the fuselage skin and rapid
decompression of the airplane.
Related AD
On January 16, 1990, we issued AD
90–06–09, amendment 39–6488 (55 FR
8370, March 7, 1990), applicable to
certain Boeing Model 727 series
airplanes. That AD requires
incorporation of certain structural
modifications. That AD was prompted
by reports of incidents involving fatigue
cracking and corrosion in transport
category airplanes that are approaching
or have exceeded their design life goal.
Relevant Service Information
We have reviewed Boeing Alert
Service Bulletin (ASB), 727–53A0153,
Revision 7, dated August 14, 2003. For
certain airplanes, the ASB describes
procedures for accomplishing repetitive
high frequency eddy current (HFEC)
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Federal Register / Vol. 70, No. 119 / Wednesday, June 22, 2005 / Proposed Rules
inspections and dimensional
inspections to detect anomalies (e.g.,
minimum geometry requirements,
jagged edges, chafing, nicks, or gouges)
of the web cutouts at stringers S–15L
and S–16L of the forward frame of the
forward entry doorway. The ASB also
describes repetitive HFEC inspections to
detect cracking of the frame web, web
assembly, and frame outer chord of the
forward frame of the forward entry
doorway, and repair procedures for
cracking within certain limits. The ASB
also specifies certain ‘‘optional’’
inspection methods to detect cracking
(visual detailed, eddy current,
penetrant, or X-Ray inspection).
Additionally, the ASB describes
procedures for an optional terminating
modification that eliminates the need to
perform the repetitive inspections.
Accomplishing the actions specified in
the service information is intended to
adequately address the identified 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 exist or
develop on other products of this same
type design. Therefore, we are
proposing this AD, which would
supersede AD 91–09–07. This proposed
AD would continue to require repetitive
visual inspections of the forward frame
of the forward entry doorway for cracks.
For certain airplanes, this proposed AD
also would require a one-time HFEC
inspection for cracks and a one-time
dimensional inspection for anomalies of
the web cutouts at stringers S–15L and
S–16L. The proposed AD also would
require repetitive HFEC inspections for
cracking of the frame web and outer
chord between stringer S–14L and the
floor, and corrective action if necessary.
Since cracking has been reported on
airplanes not specified in the previous
AD, we have added those airplanes to
the applicability of this proposed AD.
Additionally, the proposed AD would
require accomplishing the modification
for airplanes that have not
accomplished the previous optional
modification. The modification
terminates the repetitive inspection
requirements of the proposed AD. This
proposed AD would require you to use
the service information described
previously to perform these actions,
except as discussed under ‘‘Differences
Between the Proposed AD and the
Service Bulletin.’’
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Differences Between the Proposed AD
and the Service Bulletin
Although Boeing ASB 727–53A0153,
Revision 7, dated August 14, 2003,
specifies accomplishing repetitive
dimensional inspections of the web
cutouts, this proposed AD would
require those specific inspections to be
accomplished only one time, as well as
applicable corrective actions. We have
determined that, since the purpose of
the inspection is to resolve any
structural interference of static
structure, it need not be inspected again.
Although the Boeing ASB also describes
certain ‘‘optional’’ inspections in lieu of
certain HFEC inspections, this proposed
AD would require accomplishing the
HFEC inspections. (Compliance times in
Revision 7 are based on performing the
HFEC inspections, and no compliance
times were specified for the ‘‘optional’’
inspections.) Operators should also note
that the Boeing ASB specifies a grace
period for the compliance time of one
year. However, this proposed AD
specifies a grace period of 1,800 flight
cycles because cyclic loading is the
mechanism of crack propagation, rather
than calendar time. Additionally, where
the ASB specifies that operators may
contact the manufacturer for disposition
of certain repair conditions, this
proposed AD would require operators to
repair those conditions per a method
approved by the Manager, Seattle
Aircraft Certification Office (ACO),
FAA. The differences between the ASB
and the proposed AD have been
coordinated with the manufacturer.
Change to Existing AD
This proposed AD would retain
certain requirements of AD 91–09–07.
Since AD 91–09–07 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
Requirement in AD
91–09–07
Paragraph (a) ............
Paragraph (b) ............
Corresponding
requirement in this
proposed AD
Paragraph (f).
Paragraph (g).
Costs of Compliance
There are about 1,038 Model 727
series airplanes of the affected design in
the worldwide fleet. This proposed AD
would affect about 616 airplanes of U.S.
registry.
The actions that are required by AD
91–09–07 and retained in this proposed
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AD take about 58 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 $3,770 per airplane,
per inspection cycle.
The new inspections would take
about 5 to 6 work hours per airplane,
depending on the airplane
configuration, at an average labor rate of
$65 per work hour. Based on these
figures, the estimated cost of the new
actions specified in the new inspections
proposed in this AD is between $325
and $390 per airplane, per inspection
cycle.
The terminating action proposed by
this AD would affect airplanes on which
the previous optional modification has
not been accomplished, and would take
between 14 and 40 work hours per
airplane, depending on the airplane
configuration, at an average labor rate of
$65 per work hour. Required parts for
proposed terminating modification
would cost between $877 and $6,749
per airplane, depending on the airplane
configuration. Based on these figures,
the estimated cost of the terminating
action specified in this proposed AD is
between $1,787 and $9,349 per airplane.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
Section 106, describes the authority of
the FAA Administrator. Subtitle VII,
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in Subtitle VII,
Part A, Subpart III, Section 44701,
‘‘General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
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
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.
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Federal Register / Vol. 70, No. 119 / Wednesday, June 22, 2005 / Proposed Rules
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. 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.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing amendment 39–6982 (56 FR
18687, April 24, 1991) and adding the
following new airworthiness directive
(AD):
Boeing: Docket No. FAA–2005–21593;
Directorate Identifier 2002–NM–328–AD.
Comments Due Date
(a) The Federal Aviation Administration
must receive comments on this airworthiness
directive (AD) action by August 8, 2005.
Affected ADs
(b) This AD supersedes AD 91–09–07,
amendment 39–6982 (56 FR 18687, April 24,
1991).
Applicability
(c) This AD applies to Model 727 series
airplanes, certificated in any category; as
identified in Boeing Alert Service Bulletin
727–53A0153, Revision 7, dated August 14,
2003.
Unsafe Condition
(d) This AD was prompted by reports of
cracking of the forward frame of the forward
entry doorway of airplanes previously
modified. We are issuing this AD to prevent
the loss of the structural integrity of the
forward entry doorway due to cracking at
Body Station (BS) 303.9, and consequent
cracking of the fuselage skin and rapid
decompression of the airplane.
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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.
Restatement of Certain Requirements of AD
91–09–07
(f) For airplanes listed in Boeing Service
Bulletin 727–53–0153, Revision 5, dated
December 14, 1989: Visually inspect the
forward entry doorway frame for cracks in
accordance with Boeing Service Bulletin
727–53–0153, dated February 1, 1980, or
Revisions 1 though 5, at the earlier of the
times indicated in subparagraphs (a)(1) or
(a)(2) of this AD. Repeat the inspection at
intervals not to exceed 3,700 landings until
accomplishment of the one-time high
frequency eddy current (HFEC) inspection for
cracking and the one-time dimensional
inspection for anomalies required by
paragraph (i) of this AD, or the one-time
dimensional inspection for anomalies and
the initial HFEC inspection for cracking of
the forward frame of the forward entry
doorway at BS303.9 specified in paragraph
(h) of this AD, as applicable.
(1) Within the next 1,850 landings after
March 11, 1983 (the effective date of AD 83–
03–01, amendment 39–4561), or prior to
accumulating a total of 25,000 landings,
whichever occurs later; or
(2) Within the next 1,850 landings after
May 16, 1986 (the effective date of AD 83–
03–01 R1, amendment 39–5283), or prior to
accumulating a total of 15,000 landings,
whichever occurs later.
(g) For airplanes modified in accordance
with Boeing Service Bulletin 727–53–0153,
dated February 1, 1980; through Revision 4,
dated November 8, 1985; conduct the
inspections described in paragraph (f) of this
AD prior to the accumulation of 10,000
landings after the modification or within the
next 3,700 landings after May 28, 1991 (the
effective date of AD 91–09–07), whichever
occurs later. Repeat the inspection at
intervals not to exceed 3,700 landings until
accomplishment of the one-time HFEC
inspection for cracking and the one-time
dimensional inspection for anomalies
required by paragraph (i) of this AD, or the
one-time dimensional inspection for
anomalies and the initial HFEC inspection
for cracking of the forward frame of the
forward entry doorway at BS303.9 specified
in paragraph (h) of this AD, as applicable.
New Requirements of This AD
Repetitive Inspections for Certain Airplanes
(h) For Group l airplanes as defined by
Boeing Alert Service Bulletin (ASB) 727–
53A0153, Revision 7, dated August 14, 2003,
with the exception of certain Group 1
airplanes specified in paragraph (i) of this
AD: Perform a one-time dimensional
inspection for anomalies (e.g., minimum
dimension requirements, jagged edges,
chaffing, nicks, or gouges) of the web cutouts
at stringers S–15 and S–16, and HFEC
inspections for cracking of the forward frame
of the forward entry doorway at BS 303.9; in
accordance with Figure 1 of the
Accomplishment Instructions of Revision 7
of the ASB at the times specified in
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paragraph (h)(1) or (h)(2) of this AD, as
applicable. With the exception of the onetime dimensional inspection (Step 1 of
Figure 1) of the web cutouts at S–15L and S–
16L, repeat the HFEC inspections for
cracking of the forward frame of the forward
entry doorway at BS 303.9 at intervals not to
exceed 3,700 flight cycles until the
requirements of paragraph (l) of this AD have
been accomplished.
(1) For Group 1 airplanes that have not
been modified or repaired in accordance with
any issue of the service bulletin through
Revision 7 inclusive: Perform the inspection
before the accumulation of 15,000 total flight
cycles, or within 1,800 flight cycles after the
effective date of this AD, whichever occurs
later.
(2) For Group 1 airplanes that have been
modified in accordance with Repair Kit
65C20303–1 in accordance with any issue of
the service bulletin through Revision 4
inclusive: Perform the inspection before the
accumulation of 10,000 flight cycles after the
modification, or within 1,800 flight cycles
after the effective date of this AD, whichever
occurs later.
One-Time Inspections and Terminating
Actions for Certain Other Airplanes
(i) For Group 1 airplanes, as defined by
Boeing ASB 727–53A0153, Revision 7, dated
August 14, 2003, that have been modified in
accordance with Revision 5 or 6 of Boeing
Service Bulletin 727–53–0153, or that have
been repaired in accordance with Boeing
Repair Kits 65C20303–8 or –25 as specified
in Revision 2 through Revision 6 inclusive of
the service bulletin: Within 4,500 flight
cycles after the effective date of this AD, do
a one-time HFEC for cracking and a
dimensional inspection for any anomaly (e.g.,
minimum dimension requirements, jagged
edges, chaffing, nicks or gouges) of the web
cutouts at stringers S–15L and S–16L of the
forward frame of the forward entry doorway
at BS 303.9, in accordance with Step 1 and
Step 2 of Figure 1 of the Accomplishment
Instructions of Revision 7 of the ASB. For
these airplanes, accomplishment of the
HFEC, dimensional inspections, and any
applicable corrective actions, constitute
terminating actions for all the repetitive
inspection requirements of this AD.
Inspections for Group 2 Airplanes
(j) For Group 2 airplanes, as defined by
Boeing ASB 727–53A0153, Revision 7, dated
August 14, 2003, that have not been modified
or repaired in accordance with Revision 7 of
the service bulletin: Before the accumulation
of 17,000 total flight cycles, or within 4,500
flight cycles after the effective date of this
AD, whichever occurs later, perform a onetime dimensional inspection for anomalies
(e.g., minimum dimension requirements,
jagged edges, chafing, nicks, or gouges) of the
web cutouts at stringers S–15 and S–16, and
HFEC inspections for cracking of the forward
frame of the forward entry doorway at BS
303.9; in accordance with Figure 2 of the
Accomplishment Instructions of Revision 7
of the ASB. With the exception of the onetime dimensional inspection (Step 1 of
Figure 2) of the web cutouts at S–15L and S–
16L, repeat the HFEC inspections for
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cracking of the forward frame of the forward
entry doorway at BS 303.9 at intervals not to
exceed 3,700 flight cycles until the
requirements of paragraph (l) of this AD have
been accomplished.
Corrective Actions
(k) If any cracking is detected during any
HFEC inspection, or any anomaly is detected
during any dimensional inspection required
by this AD: Before further flight, accomplish
the actions in paragraph (k)(1) or (k)(2) of this
AD, as applicable.
(1) For any cracking that is within the
limits specified in the Accomplishment
Instructions of Boeing ASB 727–53A0153,
Revision 7, dated August 14, 2003: Repair the
cracking in accordance with the Revision 7
of the ASB.
(2) For any cracking that is outside the
limits specified in the Accomplishment
Instructions of the ASB or for any anomaly
that is detected during any dimensional
inspection required by this AD: Repair in
accordance with a method approved by the
Manager, Seattle Aircraft Certification (ACO),
FAA; or in accordance with data meeting the
type certification basis of the airplane
approved by an Authorized Representative
for the Boeing Delegation Option
Authorization Organization who has been
authorized by the FAA 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 reference this AD.
Alternative Methods of Compliance (AMOCs)
(m)(1) The Manager, Seattle ACO, has the
authority to approve AMOCs for this AD, if
requested in accordance with the procedures
found in 14 CFR 39.19.
(2) 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 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.
(3) AMOCs approved previously in
accordance with AD 91–09–07, amendment
39–6982, are approved as AMOCs with the
corresponding requirements and provisions
of this AD.
(4) Accomplishment of the actions
specified in paragraph (l) of this AD
constitutes an AMOC with paragraph (A) of
AD 90–06–09, amendment 39–6488, only for
the structural modification requirements
specified in Boeing Service Bulletin 727–53–
0153, Revision 4 or earlier revisions.
Issued in Renton, Washington, on June 10,
2005.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 05–12297 Filed 6–21–05; 8:45 am]
BILLING CODE 4910–13–P
Terminating Actions for Certain Airplanes
(l) For airplanes specified in paragraph
(l)(1) or (l)(2) of this AD: Prior to the
accumulation of 60,000 total flight cycles, or
within 1,800 flight cycles after the effective
date of this AD, whichever occurs later,
perform the inspections specified in Figure 1
or Figure 2, as applicable, of Revision 7 of
Boeing ASB 727–53A0153, dated August 14,
2003, and as specified by paragraph (h) or (j)
of this AD, as applicable. Before further
flight, following the inspections, modify the
forward frame in accordance with the
Accomplishment Instructions of Revision 7
of the ASB. Concurrent accomplishment of
the inspections and modification constitutes
terminating action for the repetitive
inspections required by this AD.
(1) Group 1 airplanes that have not been
modified or repaired in accordance with
Boeing Repair Kits 65C20303–8 or –25, as
specified in Boeing Service Bulletin 727–53–
0153, Revision 2, dated December 3, 1982;
Revision 3, dated June 17, 1983; Revision 4,
dated November 8, 1985; Revision 5, dated
December 14, 1989; Revision 6, dated August
27, 1992; or Revision 7 of Boeing ASB 727–
53A0153, dated August 14, 2003.
(2) Group 2 airplanes that have not been
repaired or modified in accordance with
Revision 7 of Boeing ASB 727–53A0153,
dated August 14, 2003.
Note 1: Accomplishment of the terminating
actions specified in paragraphs (i) or (l) of
this AD does not relieve the operator of
responsibility to comply with the inspection
requirements of the operator’s standard
structural maintenance program.
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–21599; Directorate
Identifier 2005–NM–036–AD]
RIN 2120–AA64
Airworthiness Directives; Bombardier
Model CL–600–2B19 (Regional Jet
Series 100 & 440) Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: The FAA proposes to
supersede an existing airworthiness
directive (AD) that applies to all
Bombardier Model CL–600–2B19 series
airplanes. The existing AD currently
requires revising the Airplane Flight
Manual (AFM) to provide the flightcrew
with operating limitations and
procedures to enable them to maintain
controllability of the airplane in the
event that aileron control stiffness is
encountered during flight. This
proposed AD would revise the
Airworthiness Limitations section of the
Instructions of Continued Airworthiness
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36067
to incorporate certain repetitive tasks for
the aileron control system and would
require a briefing to advise flight crews
that certain aileron control checks are
no longer required. After accomplishing
the applicable initial tasks, the existing
AFM revisions for the aileron control
check may be removed from the AFM.
This proposed AD is prompted by the
development of terminating actions for
the AFM revisions. We are proposing
this AD to prevent aileron control
stiffness during flight, which could
result in reduced or possible loss of
controllability of the airplane.
DATES: We must receive comments on
this proposed AD by July 22, 2005.
ADDRESSES: Use one of the following
addresses to submit comments on this
proposed 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.
For service information identified in
this proposed AD, contact Bombardier,
Inc., Canadair, Aerospace Group, P.O.
Box 6087, Station Centre-ville,
Montreal, Quebec H3C 3G9, Canada.
You can examine the contents of this
AD docket on the Internet at https://
dms.dot.gov, or in person at the Docket
Management Facility, U.S. Department
of Transportation, 400 Seventh Street
SW., room PL–401, on the plaza level of
the Nassif Building, Washington, DC.
This docket number is FAA–2005–
21599; the directorate identifier for this
docket is 2005–NM–036–AD.
FOR FURTHER INFORMATION CONTACT: Dan
Parillo, Aerospace Engineer, Systems
and Flight Test Branch, ANE–172, FAA,
New York Aircraft Certification Office,
1600 Stewart Avenue, Westbury, suite
410, New York 11590; telephone (516)
228–7305; fax (516) 794–5531.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to submit any relevant
written data, views, or arguments
regarding this proposed AD. Send your
comments to an address listed under
ADDRESSES. Include ‘‘Docket No. FAA–
E:\FR\FM\22JNP1.SGM
22JNP1
]]>Agencies
[Federal Register Volume 70, Number 119 (Wednesday, June 22, 2005)]
[Proposed Rules]
[Pages 36064-36067]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-12297]
[[Page 36064]]
=======================================================================
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-21593; Directorate Identifier 2002-NM-328-AD]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 727 Series Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to supersede an existing airworthiness
directive (AD) for certain Boeing Model 727 series airplanes. That AD
currently requires repetitive visual inspections for cracking of the
forward entry doorway forward frame and repair if necessary. That AD
also provides an optional modification that constitutes terminating
action. This proposed AD would require adding new post-repair and post-
modification inspections for previously repaired or modified airplanes,
mandating the optional modification, and adding airplanes to the
applicability of the AD. This proposed AD is prompted by reports of
cracking of the forward entry doorway forward frame of airplanes
previously modified. We are proposing this AD to prevent the loss of
the structural integrity of the forward entry doorway due to cracking
of the frame at BS 303.9, and consequent cracking of the fuselage skin
and rapid decompression of the airplane.
DATES: We must receive comments on this proposed AD by August 8, 2005.
ADDRESSES: Use one of the following addresses to submit comments on
this proposed 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.
For service information identified in this proposed AD, contact
Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-
2207.
You can examine the contents of this AD docket on the Internet at
https://dms.dot.gov, or at the Docket Management Facility, U.S.
Department of Transportation, 400 Seventh Street SW., room PL-401, on
the plaza level of the Nassif Building, Washington, DC. This docket
number is FAA-2005-21593; the directorate identifier for this docket is
2002-NM-328-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:
Comments Invited
We invite you to submit any written relevant data, views, or
arguments regarding this proposed AD. Send your comments to an address
listed under ADDRESSES. Include ``Docket No. FAA-2005-21593;
Directorate Identifier 2002-NM-328-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the proposed AD. We will
consider all comments received by the closing date and may amend the
proposed AD in light of those comments.
We will post all comments we receive, without change, to https://
dms.dot.gov, including any personal information you provide. We will
also post a report summarizing each substantive verbal contact with FAA
personnel concerning this proposed AD. Using the search function of our
docket web site, anyone can find and read the comments in any of our
dockets, including the name of the individual who sent the comment (or
signed the comment on behalf of an association, business, labor union,
etc.). You can review the DOT's complete Privacy Act Statement in the
Federal Register published on April 11, 2000 (65 FR 19477-78), or you
can visit https://dms.dot.gov.
Examining the Docket
You can examine the AD docket 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 DOT street address stated in the ADDRESSES section.
Comments will be available in the AD docket shortly after the DMS
receives them.
Discussion
On April 11, 1991, we issued AD 91-09-07, amendment 39-6982 (56 FR
18687, April 24, 1991), applicable to certain Boeing Model 727 series
airplanes. That AD requires repetitive visual inspections for cracking
of the forward entry doorway forward frame and repair if necessary.
That AD also provides an optional modification that constitutes
terminating action. That action was prompted by reports of cracking of
the forward entry doorway forward frame of airplanes previously
modified. We issued that AD to prevent loss of the structural integrity
of the forward entry doorway.
Actions Since Existing AD Was Issued
Since we issued AD 91-09-07, we have received several reports
indicating cracking found on certain frames of certain Boeing Model 727
series airplanes. The cracks were found on airplanes that had
accomplished the optional terminating action specified in AD 91-09-07.
Those airplanes had between 32,000 and 35,000 total flight cycles, and
ranged between 0.25 inch and 0.50 inch long. The cracks initiated from
the web cut-outs at stringer S-16L at Body Station (BS) 303.9, and were
typically found during routine maintenance. Additionally, cracking was
also reported on certain Model 727 series airplanes that were not
included in the applicability of AD 91-09-07. The cracking is primarily
attributed to cyclic fatigue loading at the frame web cut-outs.
Cracking of the frames, if not corrected, could result in loss of the
structural integrity of the forward entry doorway forward frame, and
consequent cracking of the fuselage skin and rapid decompression of the
airplane.
Related AD
On January 16, 1990, we issued AD 90-06-09, amendment 39-6488 (55
FR 8370, March 7, 1990), applicable to certain Boeing Model 727 series
airplanes. That AD requires incorporation of certain structural
modifications. That AD was prompted by reports of incidents involving
fatigue cracking and corrosion in transport category airplanes that are
approaching or have exceeded their design life goal.
Relevant Service Information
We have reviewed Boeing Alert Service Bulletin (ASB), 727-53A0153,
Revision 7, dated August 14, 2003. For certain airplanes, the ASB
describes procedures for accomplishing repetitive high frequency eddy
current (HFEC)
[[Page 36065]]
inspections and dimensional inspections to detect anomalies (e.g.,
minimum geometry requirements, jagged edges, chafing, nicks, or gouges)
of the web cutouts at stringers S-15L and S-16L of the forward frame of
the forward entry doorway. The ASB also describes repetitive HFEC
inspections to detect cracking of the frame web, web assembly, and
frame outer chord of the forward frame of the forward entry doorway,
and repair procedures for cracking within certain limits. The ASB also
specifies certain ``optional'' inspection methods to detect cracking
(visual detailed, eddy current, penetrant, or X-Ray inspection).
Additionally, the ASB describes procedures for an optional terminating
modification that eliminates the need to perform the repetitive
inspections. Accomplishing the actions specified in the service
information is intended to adequately address the identified 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 exist or develop on other products
of this same type design. Therefore, we are proposing this AD, which
would supersede AD 91-09-07. This proposed AD would continue to require
repetitive visual inspections of the forward frame of the forward entry
doorway for cracks. For certain airplanes, this proposed AD also would
require a one-time HFEC inspection for cracks and a one-time
dimensional inspection for anomalies of the web cutouts at stringers S-
15L and S-16L. The proposed AD also would require repetitive HFEC
inspections for cracking of the frame web and outer chord between
stringer S-14L and the floor, and corrective action if necessary. Since
cracking has been reported on airplanes not specified in the previous
AD, we have added those airplanes to the applicability of this proposed
AD. Additionally, the proposed AD would require accomplishing the
modification for airplanes that have not accomplished the previous
optional modification. The modification terminates the repetitive
inspection requirements of the proposed AD. This proposed AD would
require you to use the service information described previously to
perform these actions, except as discussed under ``Differences Between
the Proposed AD and the Service Bulletin.''
Differences Between the Proposed AD and the Service Bulletin
Although Boeing ASB 727-53A0153, Revision 7, dated August 14, 2003,
specifies accomplishing repetitive dimensional inspections of the web
cutouts, this proposed AD would require those specific inspections to
be accomplished only one time, as well as applicable corrective
actions. We have determined that, since the purpose of the inspection
is to resolve any structural interference of static structure, it need
not be inspected again. Although the Boeing ASB also describes certain
``optional'' inspections in lieu of certain HFEC inspections, this
proposed AD would require accomplishing the HFEC inspections.
(Compliance times in Revision 7 are based on performing the HFEC
inspections, and no compliance times were specified for the
``optional'' inspections.) Operators should also note that the Boeing
ASB specifies a grace period for the compliance time of one year.
However, this proposed AD specifies a grace period of 1,800 flight
cycles because cyclic loading is the mechanism of crack propagation,
rather than calendar time. Additionally, where the ASB specifies that
operators may contact the manufacturer for disposition of certain
repair conditions, this proposed AD would require operators to repair
those conditions per a method approved by the Manager, Seattle Aircraft
Certification Office (ACO), FAA. The differences between the ASB and
the proposed AD have been coordinated with the manufacturer.
Change to Existing AD
This proposed AD would retain certain requirements of AD 91-09-07.
Since AD 91-09-07 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
------------------------------------------------------------------------
Corresponding requirement
Requirement in AD 91-09-07 in this proposed AD
------------------------------------------------------------------------
Paragraph (a)............................. Paragraph (f).
Paragraph (b)............................. Paragraph (g).
------------------------------------------------------------------------
Costs of Compliance
There are about 1,038 Model 727 series airplanes of the affected
design in the worldwide fleet. This proposed AD would affect about 616
airplanes of U.S. registry.
The actions that are required by AD 91-09-07 and retained in this
proposed AD take about 58 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 $3,770 per airplane, per
inspection cycle.
The new inspections would take about 5 to 6 work hours per
airplane, depending on the airplane configuration, at an average labor
rate of $65 per work hour. Based on these figures, the estimated cost
of the new actions specified in the new inspections proposed in this AD
is between $325 and $390 per airplane, per inspection cycle.
The terminating action proposed by this AD would affect airplanes
on which the previous optional modification has not been accomplished,
and would take between 14 and 40 work hours per airplane, depending on
the airplane configuration, at an average labor rate of $65 per work
hour. Required parts for proposed terminating modification would cost
between $877 and $6,749 per airplane, depending on the airplane
configuration. Based on these figures, the estimated cost of the
terminating action specified in this proposed AD is between $1,787 and
$9,349 per airplane.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation 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 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.
[[Page 36066]]
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. 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 FAA amends Sec. 39.13 by removing amendment 39-6982 (56 FR
18687, April 24, 1991) and adding the following new airworthiness
directive (AD):
Boeing: Docket No. FAA-2005-21593; Directorate Identifier 2002-NM-
328-AD.
Comments Due Date
(a) The Federal Aviation Administration must receive comments on
this airworthiness directive (AD) action by August 8, 2005.
Affected ADs
(b) This AD supersedes AD 91-09-07, amendment 39-6982 (56 FR
18687, April 24, 1991).
Applicability
(c) This AD applies to Model 727 series airplanes, certificated
in any category; as identified in Boeing Alert Service Bulletin 727-
53A0153, Revision 7, dated August 14, 2003.
Unsafe Condition
(d) This AD was prompted by reports of cracking of the forward
frame of the forward entry doorway of airplanes previously modified.
We are issuing this AD to prevent the loss of the structural
integrity of the forward entry doorway due to cracking at Body
Station (BS) 303.9, and consequent cracking of the fuselage skin and
rapid decompression of the airplane.
Compliance
(e) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Restatement of Certain Requirements of AD 91-09-07
(f) For airplanes listed in Boeing Service Bulletin 727-53-0153,
Revision 5, dated December 14, 1989: Visually inspect the forward
entry doorway frame for cracks in accordance with Boeing Service
Bulletin 727-53-0153, dated February 1, 1980, or Revisions 1 though
5, at the earlier of the times indicated in subparagraphs (a)(1) or
(a)(2) of this AD. Repeat the inspection at intervals not to exceed
3,700 landings until accomplishment of the one-time high frequency
eddy current (HFEC) inspection for cracking and the one-time
dimensional inspection for anomalies required by paragraph (i) of
this AD, or the one-time dimensional inspection for anomalies and
the initial HFEC inspection for cracking of the forward frame of the
forward entry doorway at BS303.9 specified in paragraph (h) of this
AD, as applicable.
(1) Within the next 1,850 landings after March 11, 1983 (the
effective date of AD 83-03-01, amendment 39-4561), or prior to
accumulating a total of 25,000 landings, whichever occurs later; or
(2) Within the next 1,850 landings after May 16, 1986 (the
effective date of AD 83-03-01 R1, amendment 39-5283), or prior to
accumulating a total of 15,000 landings, whichever occurs later.
(g) For airplanes modified in accordance with Boeing Service
Bulletin 727-53-0153, dated February 1, 1980; through Revision 4,
dated November 8, 1985; conduct the inspections described in
paragraph (f) of this AD prior to the accumulation of 10,000
landings after the modification or within the next 3,700 landings
after May 28, 1991 (the effective date of AD 91-09-07), whichever
occurs later. Repeat the inspection at intervals not to exceed 3,700
landings until accomplishment of the one-time HFEC inspection for
cracking and the one-time dimensional inspection for anomalies
required by paragraph (i) of this AD, or the one-time dimensional
inspection for anomalies and the initial HFEC inspection for
cracking of the forward frame of the forward entry doorway at
BS303.9 specified in paragraph (h) of this AD, as applicable.
New Requirements of This AD
Repetitive Inspections for Certain Airplanes
(h) For Group l airplanes as defined by Boeing Alert Service
Bulletin (ASB) 727-53A0153, Revision 7, dated August 14, 2003, with
the exception of certain Group 1 airplanes specified in paragraph
(i) of this AD: Perform a one-time dimensional inspection for
anomalies (e.g., minimum dimension requirements, jagged edges,
chaffing, nicks, or gouges) of the web cutouts at stringers S-15 and
S-16, and HFEC inspections for cracking of the forward frame of the
forward entry doorway at BS 303.9; in accordance with Figure 1 of
the Accomplishment Instructions of Revision 7 of the ASB at the
times specified in paragraph (h)(1) or (h)(2) of this AD, as
applicable. With the exception of the one-time dimensional
inspection (Step 1 of Figure 1) of the web cutouts at S-15L and S-
16L, repeat the HFEC inspections for cracking of the forward frame
of the forward entry doorway at BS 303.9 at intervals not to exceed
3,700 flight cycles until the requirements of paragraph (l) of this
AD have been accomplished.
(1) For Group 1 airplanes that have not been modified or
repaired in accordance with any issue of the service bulletin
through Revision 7 inclusive: Perform the inspection before the
accumulation of 15,000 total flight cycles, or within 1,800 flight
cycles after the effective date of this AD, whichever occurs later.
(2) For Group 1 airplanes that have been modified in accordance
with Repair Kit 65C20303-1 in accordance with any issue of the
service bulletin through Revision 4 inclusive: Perform the
inspection before the accumulation of 10,000 flight cycles after the
modification, or within 1,800 flight cycles after the effective date
of this AD, whichever occurs later.
One-Time Inspections and Terminating Actions for Certain Other
Airplanes
(i) For Group 1 airplanes, as defined by Boeing ASB 727-53A0153,
Revision 7, dated August 14, 2003, that have been modified in
accordance with Revision 5 or 6 of Boeing Service Bulletin 727-53-
0153, or that have been repaired in accordance with Boeing Repair
Kits 65C20303-8 or -25 as specified in Revision 2 through Revision 6
inclusive of the service bulletin: Within 4,500 flight cycles after
the effective date of this AD, do a one-time HFEC for cracking and a
dimensional inspection for any anomaly (e.g., minimum dimension
requirements, jagged edges, chaffing, nicks or gouges) of the web
cutouts at stringers S-15L and S-16L of the forward frame of the
forward entry doorway at BS 303.9, in accordance with Step 1 and
Step 2 of Figure 1 of the Accomplishment Instructions of Revision 7
of the ASB. For these airplanes, accomplishment of the HFEC,
dimensional inspections, and any applicable corrective actions,
constitute terminating actions for all the repetitive inspection
requirements of this AD.
Inspections for Group 2 Airplanes
(j) For Group 2 airplanes, as defined by Boeing ASB 727-53A0153,
Revision 7, dated August 14, 2003, that have not been modified or
repaired in accordance with Revision 7 of the service bulletin:
Before the accumulation of 17,000 total flight cycles, or within
4,500 flight cycles after the effective date of this AD, whichever
occurs later, perform a one-time dimensional inspection for
anomalies (e.g., minimum dimension requirements, jagged edges,
chafing, nicks, or gouges) of the web cutouts at stringers S-15 and
S-16, and HFEC inspections for cracking of the forward frame of the
forward entry doorway at BS 303.9; in accordance with Figure 2 of
the Accomplishment Instructions of Revision 7 of the ASB. With the
exception of the one-time dimensional inspection (Step 1 of Figure
2) of the web cutouts at S-15L and S-16L, repeat the HFEC
inspections for
[[Page 36067]]
cracking of the forward frame of the forward entry doorway at BS
303.9 at intervals not to exceed 3,700 flight cycles until the
requirements of paragraph (l) of this AD have been accomplished.
Corrective Actions
(k) If any cracking is detected during any HFEC inspection, or
any anomaly is detected during any dimensional inspection required
by this AD: Before further flight, accomplish the actions in
paragraph (k)(1) or (k)(2) of this AD, as applicable.
(1) For any cracking that is within the limits specified in the
Accomplishment Instructions of Boeing ASB 727-53A0153, Revision 7,
dated August 14, 2003: Repair the cracking in accordance with the
Revision 7 of the ASB.
(2) For any cracking that is outside the limits specified in the
Accomplishment Instructions of the ASB or for any anomaly that is
detected during any dimensional inspection required by this AD:
Repair in accordance with a method approved by the Manager, Seattle
Aircraft Certification (ACO), FAA; or in accordance with data
meeting the type certification basis of the airplane approved by an
Authorized Representative for the Boeing Delegation Option
Authorization Organization who has been authorized by the FAA 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 reference this AD.
Terminating Actions for Certain Airplanes
(l) For airplanes specified in paragraph (l)(1) or (l)(2) of
this AD: Prior to the accumulation of 60,000 total flight cycles, or
within 1,800 flight cycles after the effective date of this AD,
whichever occurs later, perform the inspections specified in Figure
1 or Figure 2, as applicable, of Revision 7 of Boeing ASB 727-
53A0153, dated August 14, 2003, and as specified by paragraph (h) or
(j) of this AD, as applicable. Before further flight, following the
inspections, modify the forward frame in accordance with the
Accomplishment Instructions of Revision 7 of the ASB. Concurrent
accomplishment of the inspections and modification constitutes
terminating action for the repetitive inspections required by this
AD.
(1) Group 1 airplanes that have not been modified or repaired in
accordance with Boeing Repair Kits 65C20303-8 or -25, as specified
in Boeing Service Bulletin 727-53-0153, Revision 2, dated December
3, 1982; Revision 3, dated June 17, 1983; Revision 4, dated November
8, 1985; Revision 5, dated December 14, 1989; Revision 6, dated
August 27, 1992; or Revision 7 of Boeing ASB 727-53A0153, dated
August 14, 2003.
(2) Group 2 airplanes that have not been repaired or modified in
accordance with Revision 7 of Boeing ASB 727-53A0153, dated August
14, 2003.
Note 1: Accomplishment of the terminating actions specified in
paragraphs (i) or (l) of this AD does not relieve the operator of
responsibility to comply with the inspection requirements of the
operator's standard structural maintenance program.
Alternative Methods of Compliance (AMOCs)
(m)(1) The Manager, Seattle ACO, has the authority to approve
AMOCs for this AD, if requested in accordance with the procedures
found in 14 CFR 39.19.
(2) 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 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.
(3) AMOCs approved previously in accordance with AD 91-09-07,
amendment 39-6982, are approved as AMOCs with the corresponding
requirements and provisions of this AD.
(4) Accomplishment of the actions specified in paragraph (l) of
this AD constitutes an AMOC with paragraph (A) of AD 90-06-09,
amendment 39-6488, only for the structural modification requirements
specified in Boeing Service Bulletin 727-53-0153, Revision 4 or
earlier revisions.
Issued in Renton, Washington, on June 10, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-12297 Filed 6-21-05; 8:45 am]
BILLING CODE 4910-13-P
