Airworthiness Directives; Boeing Model 727-200 Series Airplanes Equipped With a No. 3 Cargo Door, 11345-11349 [E6-3221]
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Federal Register / Vol. 71, No. 44 / Tuesday, March 7, 2006 / Proposed Rules
Note 1: For the purposes of this AD, a
detailed inspection is defined as: ‘‘An
intensive visual examination of a specific
structural area, system, installation, or
assembly to detect damage, failure, or
irregularity. Available lighting is normally
supplemented with a direct source of good
lighting at intensity deemed appropriate by
the inspector. Inspection aids such as mirror,
magnifying lenses, etc., may be used. Surface
cleaning and elaborate access procedures
may be required.’’
Note 2: A note in the Accomplishment
Instructions of the Raytheon service bulletin
instructs operators to contact Raytheon if any
difficulty is encountered in accomplishing
the service bulletin. However, any deviation
from the instructions provided in the service
bulletin must be approved as an alternative
method of compliance (AMOC) under
paragraph (i)(1) of this AD.
Inspections Accomplished According to
Previous Issue of Service Bulletin
(g) Inspections accomplished before the
effective date of this AD according to
Raytheon Service Bulletin SB 24–3745, dated
September 2005, are considered acceptable
for compliance with the inspections specified
in paragraph (f) of this AD.
No Reporting Requirement
(h) Although the Accomplishment
Instructions of Raytheon Service Bulletin SB
24–3745, Revision 1, dated September 2005,
specify submitting certain information to the
manufacturer, this AD does not include that
requirement.
Alternative Methods of Compliance
(AMOCs)
(i)(1) The Manager, Wichita 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) Before using any AMOC approved in
accordance with § 39.19 on any airplane to
which the AMOC applies, notify the
appropriate principal inspector in the FAA
Flight Standards Certificate Holding District
Office.
Issued in Renton, Washington, on February
27, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E6–3219 Filed 3–6–06; 8:45 am]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–24073; Directorate
Identifier 2002–NM–272–AD]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 727–200 Series Airplanes
Equipped With a No. 3 Cargo Door
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 certain
Boeing Model 727–200 series airplanes.
The existing AD currently requires
initial and repetitive inspections for
cracks in the forward frame of the No.
3 cargo door cutout; and corrective
actions, if necessary. The existing AD
also provides for an optional structural
modification, which terminates the
repetitive inspections. This proposed
AD would reduce the compliance time
for the initial inspections and add an
optional method of inspection for both
the initial and repetitive inspections.
This proposed AD would also add
initial and repetitive inspections of an
additional area and repair if necessary.
Additionally, this proposed AD would
clarify that the previously optional
structural modification is now required
by other rulemaking. This proposed AD
results from additional reports of
cracking in the forward frame of the No.
3 cargo door cutout. We are proposing
this AD to detect and correct cracking of
the forward frame and fuselage skin of
the No. 3 cargo door cutout, which
could result in failure of the frame and
skin, and consequent rapid
decompression of the airplane.
DATES: We must receive comments on
this proposed AD by April 21, 2006.
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.
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• 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.
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 relevant
written data, views, or arguments
regarding this proposed AD. Include the
docket number ‘‘Docket No. FAA–2006–
24073; Directorate Identifier 2002–NM–
272–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 that 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 may
review the DOT’s complete Privacy Act
Statement in the Federal Register
published on April 11, 2000 (65 FR
19477–78), or may visit https://
dms.dot.gov.
Examining the Docket
You may 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 DOT
street address stated in the ADDRESSES
section. Comments will be available in
the AD docket shortly after the Docket
Management System receives them.
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Federal Register / Vol. 71, No. 44 / Tuesday, March 7, 2006 / Proposed Rules
Discussion
On August 10, 1987, we issued AD
86–17–05 R1, amendment 39–5714 (52
FR 32534, August 28, 1987), for certain
Boeing Model 727–200 series airplanes.
AD 86–17–05 R1 requires initial and
repetitive visual inspections of the
forward frame of the No. 3 cargo door
cutout for cracks, and repair of any
crack detected. That AD also provides
for optional structural modification of
uncracked frames, which terminates the
repetitive inspections.
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Actions Since Existing AD Was Issued
Since we issued AD 86–17–05 R1, we
have received reports indicating that the
frame of the No. 3 cargo door cutout was
severed on two Model 727–200 series
airplanes. Both airplanes had
accumulated approximately 24,500 total
flight cycles (i.e., approximately 4,800
flight cycles fewer than the threshold
specified in AD 86–17–05 R1 for the
initial inspection of the frame.) We have
determined that this damage was a
result of fatigue cracking. Cracking of
the forward frame of the No. 3 cargo
door cutout, if not corrected, can result
in failure of the forward frame of the No.
3 cargo door cutout and consequent
rapid decompression of the airplane.
Other Relevant Rulemaking
Also since the issuance of AD 86–17–
05 R1, we issued AD 90–06–09,
amendment 39–6488 (55 FR 8370,
March 7, 1990), for certain Boeing
Model 727 series airplanes. That AD
requires certain structural modifications
including a frame reinforcement
preventative modification of the forward
frame of the No. 3 cargo door cutout.
Boeing Alert Service Bulletin 727–
53A0169, Revision 1, dated March 28,
1986; Revision 2, dated May 23, 1986;
Revision 3, dated June 11, 1987; and
Revision 4, dated January 21, 1989; are
referenced in Boeing Document D6–
54860, Revision C, dated December 11,
1989 (which is referenced as the
appropriate source of service
information for accomplishing the
structural modifications in AD 90–06–
09) as acceptable sources of service
information for accomplishing the frame
reinforcement preventative modification
of the forward frame of the No. 3 cargo
door cutout. Doing the frame
reinforcement preventative modification
of the forward frame of the No. 3 cargo
door cutout, as required by paragraph A.
of AD 90–06–09, terminates the
repetitive inspections required by this
proposed AD.
Relevant Service Information
We have reviewed Boeing Service
Bulletins 727–53A0169, Revision 5,
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dated November 2, 1989; and Revision
6, dated September 28, 2002. The
service bulletins describe procedures for
an initial penetrant or visual inspection
of the forward and aft sides of the
forward frame of the No. 3 cargo door
cutout, including a portion of the
exterior skin, frame web, and inner
flanges, to find cracking; and related
investigative and corrective actions, if
necessary. The related investigative
actions include performing repetitive
inspecting if no crack is found and
following repair of any crack that is
found. The corrective actions include
contacting Boeing for repair instructions
for any crack found in the skin and
certain cracks found in the frame;
replacing any cracked segment of the
frame with a new or serviceable
segment, or repairing any crack found in
the frame and reporting certain
information to Boeing following the
repair; and inspections for repairs made
previously. The service bulletin also
describes procedures for a frame
reinforcement preventative modification
of the forward frame of the No. 3 cargo
door cutout that would eliminate the
need for the repetitive inspections.
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
The unsafe condition described
previously is likely to exist or develop
on other airplanes of the same type
design. We are proposing to supersede
AD 86–17–05 R1. This proposed AD
would continue to require initial and
repetitive inspections to find cracking in
the forward frame of the No. 3 cargo
door cutout; and corrective actions, if
necessary. This proposed AD would
reduce the compliance time for the
initial inspections and add an optional
method of inspection for both the initial
and repetitive inspections. This
proposed AD would also add an initial
and repetitive inspections of an
additional inspection area, and repair if
necessary. Additionally, this proposed
AD would clarify that the previously
optional structural modification is now
required by other rulemaking. This
proposed AD would also require you to
use the service information described
previously to perform these actions,
except as discussed under ‘‘Differences
Between the Proposed AD and Service
Information.’’
Differences Between the Proposed AD
and Service Information
The service bulletin specifies that you
may contact the manufacturer for
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instructions on how to repair certain
conditions, but this proposed AD would
require repairing those conditions in
one of the following ways:
• Using a method that we approve; or
• Using data that meet the
certification basis of the airplane, and
that have been approved by an
Authorized Representative for the
Boeing Commercial Airplanes
Delegation Option Authorization
Organization whom we have authorized
to make those findings.
Boeing Service Bulletin 727–
53A0169, Revision 6, dated September
28, 2002, only specifies a ‘‘visual
inspection’’ (in addition to the penetrant
inspection) for cracking of the forward
frame of the No. 3 cargo door cutout. We
have determined that the procedures for
this inspection in the service bulletin
should be described as a ‘‘detailed
inspection.’’ We have included Note 1
in this AD to define this type of
inspection.
Additionally, the service bulletin
describes procedures for accomplishing
a structural modification that would
terminate the repetitive inspections also
described in that service bulletin. The
service bulletin recommends
accomplishing the structural
modification prior to an airplane
accumulating 60,000 total flight cycles.
We have determined that this proposed
AD should not contain a requirement for
that terminating structural modification,
because we have previously issued AD
90–06–09, which currently requires that
structural modification for the affected
airplanes.
Although the Accomplishment
Instructions of the service bulletin
describe procedures for submitting
inspection findings to Boeing, we are
not requiring that action in this
proposed AD.
Clarification of Items Referenced in the
Service Bulletin
Paragraph 3.B.7.c. of the
Accomplishment Instructions and Step
1 of Figure 2 of Boeing Service Bulletin
727–53A0169, Revision 6, dated
September 28, 2002, refer to ‘‘Detail 1’’
and ‘‘Detail 2.’’ However, in the drawing
portion of Figure 2, those details are
labeled ‘‘Detail A’’ and Detail ‘‘B.’’
Therefore, when instructed to refer to
Detail 1 of Figure 2, operators should
refer to Detail A; when instructed to
refer to Detail 2 of Figure 2, operators
should refer to Detail B. We have
learned that Boeing intends to publish
an information notice to inform
operators of this issue.
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Federal Register / Vol. 71, No. 44 / Tuesday, March 7, 2006 / Proposed Rules
Changes to Existing AD
We have removed all references to
‘‘later FAA-approved revisions of the
applicable service bulletin’’ in the
‘‘Requirements of AD 86–17–05 R1 With
Reduced Threshold and New Optional
Inspection Method,’’ to be consistent
with FAA policy. We cannot use the
phrase, ‘‘or later FAA-approved
revisions,’’ in ADs because it violates
Office of the Federal Register
regulations for approving materials that
are incorporated by reference. However,
in paragraph (m) of this proposed AD,
we are giving operators credit for
actions done before the effective date of
this AD in accordance with Revision 2,
dated May 23, 1986; Revision 3, dated
June 11, 1987; Revision 4, dated January
21, 1988; and Revision 5, dated
November 2, 1989, of Boeing Service
Bulletin 727–53A0169. We may decide
to approve later revisions of the service
bulletin as an alternative method of
compliance with this proposed AD, as
This proposed AD would retain the
requirements of AD 86–17–05 R1
(including the requirements of AD 86–
17–05). Since AD 86–17–05 R1 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 in this
proposed AD
Requirement in AD
86–17–05 R1
Paragraph
Paragraph
Paragraph
Paragraph
A
B
C
D
..............
..............
..............
..............
Paragraph
Paragraph
Paragraph
Paragraph
(f).
(g).
(h).
(n).
provided by paragraph (p) of this
proposed AD.
We have also changed the term
‘‘landings’’ in the ‘‘Requirements of AD
86–17–05 R1 With Reduced Threshold
and New Optional Inspection Method,’’
to ‘‘flight cycles’’ to be consistent with
the new requirements of this proposed
AD. This change has no effect on the
compliance times specified in the
‘‘Requirements of AD 86–17–05 R1 With
Reduced Threshold and New Optional
Inspection Method.’’
Costs of Compliance
There are about 269 airplanes of the
affected design in the worldwide fleet.
The new requirements of this AD add
no additional economic burden. The
current costs for U.S. operators to
comply with this proposed AD are
repeated for the convenience of affected
operators, as follows:
ESTIMATED COSTS
Action
Work hours
Inspections (required by
AD 86–17–05 R1), per
inspection cycle.
Average
labor rate
per hour
6
$65
Authority for This Rulemaking
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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
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Parts cost
Cost per airplane
None ................................
Number of
U.S.-registered
airplanes
$390, per inspection cycle
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. See the ADDRESSES
section for a location to examine the
regulatory evaluation.
166
Fleet cost
$64,740, per
inspection
cycle.
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 39–5714 (52 FR
32534, August 28, 1987) and adding the
following new airworthiness directive
(AD):
Boeing: Docket No. FAA–2006–24073;
Directorate Identifier 2002–NM–272–AD.
Comments Due Date
(a) The Federal Aviation Administration
must receive comments on this AD action by
April 21, 2006.
Affected ADs
(b) This AD supersedes AD 86–17–05 R1.
The Proposed Amendment
Applicability
(c) This AD applies to Boeing Model 727–
200 series airplanes, certificated in any
category, equipped with a No. 3 cargo door,
as identified in Boeing Service Bulletin 727–
53A0169, Revision 2, dated May 23, 1986.
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
Unsafe Condition
(d) This AD results from additional reports
of cracking in the forward frame of the No.
3 cargo door cutout. We are issuing this AD
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Safety.
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Federal Register / Vol. 71, No. 44 / Tuesday, March 7, 2006 / Proposed Rules
to detect and correct cracking of the forward
frame and fuselage skin of the No. 3 cargo
door cutout, which could result in failure of
the frame and consequent 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.
Requirements of AD 86–17–05 RL With
Reduced Threshold and New Optional
Inspection Method
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Inspections
(f) At the earlier of the times specified in
paragraphs (f)(1) and (f)(2) of this AD: Do a
penetrant or detailed inspection of the
forward frame of the No. 3 cargo door cutout
for cracking, in accordance with paragraph C.
of the Accomplishment Instructions of
Boeing Service Bulletin 727–53A0169,
Revision 2, dated May 23, 1986. After the
effective date of this AD, the penetrant or
detailed inspection must be done in
accordance with paragraph 3.B.3. of the
Accomplishment Instructions of Boeing
Service Bulletin 727–53A0169, Revision 6,
dated September 28, 2002. If any cracking is
found, repair in accordance with paragraph
(h) or (l) of this AD, as applicable. Repeat the
inspection at intervals not to exceed 2,200
flight cycles, until the preventative
modification specified in paragraph (n) of
this AD is done.
(1) Within the next 300 flight cycles after
September 3, 1987 (the effective date of AD
86–17–05 R1), or prior to accumulating
29,000 total flight cycles, whichever occurs
later, unless accomplished within the last
1,900 flight cycles.
(2) Prior to accumulating 18,000 total flight
cycles, or within 2,200 flight cycles after the
effective date of this AD, whichever occurs
later.
(g) At the earlier of the times specified in
paragraphs (g)(1) and (g)(2) of this AD: Do a
detailed inspection of the forward frame of
the No. 3 cargo door cutout for cracking, in
accordance with paragraphs D. and E. of the
Accomplishment Instructions of Boeing
Service Bulletin 727–53A0169, Revision 2,
dated May 23, 1986. After the effective date
of this AD, the detailed inspection must be
done in accordance with paragraphs 3.B.4.
and 3.B.5. of the Accomplishment
Instructions of Boeing Service Bulletin 727–
53A0169, Revision 6, dated September 28,
2002. If any cracking is found, repair in
accordance with paragraph (h) or (l) of this
AD, as applicable. Repeat the inspection at
intervals not to exceed 2,200 flight cycles,
until the preventative modification specified
in paragraph (n) of this AD is done.
(1) Within the next 300 flight cycles after
September 3, 1987, or prior to accumulating
35,000 total flight cycles, whichever occurs
later, unless accomplished within the last
1,900 flight cycles.
(2) Prior to accumulating 18,000 total flight
cycles, or within 2,200 flight cycles after the
effective date of this AD, whichever occurs
later.
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Repair
(h) Before further flight, repair any crack in
the forward frame of the No. 3 cargo door
cutout found before the effective date of this
AD during any inspection required by
paragraph (f) or (g) of this AD, in accordance
with paragraph G. of the Accomplishment
Instructions in Boeing Service Bulletin 727–
53A0169, Revision 2, dated May 23, 1986.
Repeat the inspections specified in
paragraphs (f) and (g) of this AD at intervals
not to exceed 2,200 flight cycles, for all areas
of the forward frame not covered by the
repair, in accordance with the
Accomplishment Instructions of paragraphs
C., D., and E. of Boeing Service Bulletin 727–
53A0169, Revision 2, dated May 23, 1986.
New Requirements of This AD
Inspection of Repairs of the Frame Done
Before the Effective Date of the AD
(i) For any repair to the forward frame of
the No. 3 cargo door cutout done, as required
by paragraph (h) of this AD, before the
effective date of this AD: Within 18,000 flight
cycles following the repair, or 2,200 flight
cycles after the effective date of this AD,
whichever occurs later, do a detailed
inspection of the repair for cracking in
accordance with the Accomplishment
Instructions of Boeing Service Bulletin 727–
53A0169, Revision 6, dated September 28,
2002. Thereafter, repeat the inspection at
intervals not to exceed 2,200 flight cycles,
until the preventative modification specified
in paragraph (n) of this AD is done.
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.’’
New Inspections of Skin Surrounding the
Frame
(j) Prior to the accumulation of 18,000 total
flight cycles, or within 2,200 flight cycles
after the effective date of this AD, whichever
occurs later: Do a penetrant or detailed
inspection for cracking of the fuselage skin of
the No. 3 cargo door cutout between stringers
S–24 and S–27, in accordance with
paragraph 3.B.3. of the Accomplishment
Instructions of Boeing Service Bulletin 727–
53A0169, Revision 6, dated September 28,
2002. Repeat the inspection at intervals not
to exceed 2,200 flight cycles, until the
preventative modification specified in
paragraph (n) of this AD is done.
Repair of Cracked Skin
(k) If any crack is found in the fuselage
skin during any inspection required by
paragraph (j) of this AD: Before further flight,
repair the crack using a method approved in
accordance with the procedures specified in
paragraph (p) of this AD.
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Repair of Cracked Frames and Post-Repair
Inspections
(l) If, after the effective date of this AD, any
crack is found in the forward frame of the No.
3 cargo door cutout during any inspection
required by paragraph (f), (g), or (i) of this
AD: Before further flight, do the actions
specified in paragraph (l)(1), (l)(2), or (l)(3) of
this AD, as applicable. Inspect the repair
within 18,000 flight cycles following the
repair, in accordance with paragraphs 3.B.4.
and 3.B.5. of the Accomplishment
Instructions of Boeing Service Bulletin 727–
53A0169, Revision 6, dated September 28,
2002. Thereafter, repeat the inspections at
intervals not to exceed 2,200 flight cycles,
until the preventative modification specified
in paragraph (n) of this AD is done.
(1) If cracks have not severed the inner
flange, do an interim repair using a method
approved in accordance with the procedures
specified in paragraph (p) of this AD.
(2) Repair the crack in accordance with
paragraph 3.B.7.b. of the Accomplishment
Instructions of Boeing Service Bulletin 727–
53A0169, Revision 6, dated September 28,
2002.
(3) Replace the cracked segment of the
frame with a new or serviceable component
and install the frame reinforcement
preventative modification, in accordance
with paragraph 3.B.7.c. of the
Accomplishment Instructions of Boeing
Service Bulletin 727–53A0169, Revision 6,
dated September 28, 2002. This action
terminates the requirements of this AD.
Repairs Done According to Previous Issues of
the Service Bulletin
(m) Inspections and repairs done before the
effective date of this AD in accordance with
Boeing Service Bulletin 727–53A0169,
Revision 2, dated May 23, 1986; Revision 3,
dated June 11, 1987; Revision 4, dated
January 21, 1988; and Revision 5, dated
November 2, 1989, are acceptable for
compliance with the corresponding
requirements of paragraphs (h), (k), and (l) of
this AD, as applicable.
Terminating Modification Required by AD
90–06–09
(n) At the same time as the applicable
inspections provided in paragraphs (f), (g),
(i), and (j) of this AD are accomplished, doing
the frame reinforcement preventative
modification required by paragraph A. of AD
90–06–09 or the frame reinforcement
preventative modification specified in Figure
2 of Boeing Service Bulletins 727–53A0169,
Revision 5, dated November 2, 1989; and
Revision 6, dated September 28, 2002;
terminates the requirements of this AD.
Paragraph A. of AD 90–06–09 references
Boeing Document D6–54860, Revision C,
dated December 11, 1989, ‘‘Aging Airplane
Structural Modification Program—Model
727’’ as the appropriate source of service
information for accomplishing the frame
reinforcement preventative modification
(along with numerous other structural
modifications required by paragraph A. of
AD 90–06–09).
Information Submission
(o) Although the service bulletins
referenced in this AD specify to submit
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07MRP1
Federal Register / Vol. 71, No. 44 / Tuesday, March 7, 2006 / Proposed Rules
certain information to the manufacturer, this
AD does not include that requirement.
Alternative Methods of Compliance (AMOCs)
(p) (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) Before using any AMOC approved in
accordance with § 39.19 on any airplane to
which the AMOC applies, notify the
appropriate principal inspector in the FAA
Flight Standards Certificate Holding District
Office.
(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) An AMOC approved previously in
accordance with AD 86–17–05 R1, is
approved as an AMOC with the
corresponding requirements and provisions
of this AD.
Issued in Renton, Washington, on February
23, 2006.
Michael J. Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. E6–3221 Filed 3–6–06; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–24075; Directorate
Identifier 2005–NM–235–AD]
RIN 2120–AA64
Airworthiness Directives; Saab Model
SAAB-Fairchild SF340A (SAAB/
SF340A) and SAAB 340B Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
sroberts on PROD1PC70 with PROPOSALS
AGENCY:
SUMMARY: The FAA proposes to adopt a
new airworthiness directive (AD) for
certain Saab Model SAAB-Fairchild
SF340A (SAAB/SF340A) and SAAB
340B airplanes. This proposed AD
would require a one-time inspection to
see if a faulty uplock axle for the shock
strut of the main landing gear (MLG) is
installed, and replacing the uplock axle
with a new uplock axle if necessary.
This proposed AD results from a report
of a cracked uplock axle caused by
hydrogen embrittlement during the
VerDate Aug<31>2005
16:19 Mar 06, 2006
Jkt 208001
manufacturing process. We are
proposing this AD to prevent failure of
the uplock mechanism, which,
combined with a loss of hydraulic
pressure, could result in an
uncommanded extension of the MLG.
DATES: We must receive comments on
this proposed AD by April 6, 2006.
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.
Contact Saab Aircraft AB, SAAB
Aircraft Product Support, S–581.88,
¨
Linkoping, Sweden, for service
information identified in this proposed
AD.
FOR FURTHER INFORMATION CONTACT: Dan
Rodina, Aerospace Engineer,
International Branch, ANM–116, FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington
98055–4056; telephone (425) 227–2125;
fax (425) 227–1149.
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 in the
ADDRESSES section. Include the docket
number ‘‘FAA–2006–24075; Directorate
Identifier 2005–NM–235–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 that Web
site, anyone can find and read the
PO 00000
Frm 00024
Fmt 4702
Sfmt 4702
11349
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 may
review the DOT’s complete Privacy Act
Statement in the Federal Register
published on April 11, 2000 (65 FR
19477–78), or you may visit https://
dms.dot.gov.
Examining the Docket
You may 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 DOT
street address stated in the ADDRESSES
section. Comments will be available in
the AD docket shortly after the Docket
Management System receives them.
Discussion
The Luftfartsstyrelsen (LFS), which is
the airworthiness authority for Sweden,
notified us that an unsafe condition may
exist on certain Saab Model SAABFairchild SF340A (SAAB/SF340A) and
SAAB 340B airplanes. The LFS advises
that a cracked uplock axle for the shock
strut of the main landing gear (MLG) has
been found. The crack was caused by
hydrogen embrittlement during the
manufacturing process. The LFS further
advises that all uplock axles produced
in the same batch must be removed from
service and scrapped. A cracked uplock
axle, combined with a loss of hydraulic
pressure, if not corrected, could result
in an uncommanded extension of the
MLG.
Relevant Service Information
Saab has issued Saab Service Bulletin
340–32–132, dated November 3, 2005.
The service bulletin describes
procedures for inspecting the shock
strut of the MLG to see if an uplock axle
with an affected serial number is
installed, and replacing the uplock axle
with a new uplock axle if necessary.
Accomplishing the actions specified in
the service information is intended to
adequately address the unsafe
condition. The LFS mandated the
service information and issued Swedish
airworthiness directive 1–199, dated
November 9, 2005, to ensure the
continued airworthiness of these
airplanes in Sweden.
The Saab service bulletin refers to
APPH Service Bulletins AIR83022–32–
31, Revision 1; and AIR83064–32–11,
Revision 1; both dated October 2005; as
additional sources of service
E:\FR\FM\07MRP1.SGM
07MRP1
]]>Agencies
[Federal Register Volume 71, Number 44 (Tuesday, March 7, 2006)]
[Proposed Rules]
[Pages 11345-11349]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-3221]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-24073; Directorate Identifier 2002-NM-272-AD]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 727-200 Series Airplanes
Equipped With a No. 3 Cargo Door
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) that applies to certain Boeing Model 727-200 series
airplanes. The existing AD currently requires initial and repetitive
inspections for cracks in the forward frame of the No. 3 cargo door
cutout; and corrective actions, if necessary. The existing AD also
provides for an optional structural modification, which terminates the
repetitive inspections. This proposed AD would reduce the compliance
time for the initial inspections and add an optional method of
inspection for both the initial and repetitive inspections. This
proposed AD would also add initial and repetitive inspections of an
additional area and repair if necessary. Additionally, this proposed AD
would clarify that the previously optional structural modification is
now required by other rulemaking. This proposed AD results from
additional reports of cracking in the forward frame of the No. 3 cargo
door cutout. We are proposing this AD to detect and correct cracking of
the forward frame and fuselage skin of the No. 3 cargo door cutout,
which could result in failure of the frame and skin, and consequent
rapid decompression of the airplane.
DATES: We must receive comments on this proposed AD by April 21, 2006.
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.
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 relevant written data, views, or
arguments regarding this proposed AD. Include the docket number
``Docket No. FAA-2006-24073; Directorate Identifier 2002-NM-272-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
that 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 may review the DOT's complete Privacy Act Statement in the
Federal Register published on April 11, 2000 (65 FR 19477-78), or may
visit https://dms.dot.gov.
Examining the Docket
You may 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 DOT
street address stated in the ADDRESSES section. Comments will be
available in the AD docket shortly after the Docket Management System
receives them.
[[Page 11346]]
Discussion
On August 10, 1987, we issued AD 86-17-05 R1, amendment 39-5714 (52
FR 32534, August 28, 1987), for certain Boeing Model 727-200 series
airplanes. AD 86-17-05 R1 requires initial and repetitive visual
inspections of the forward frame of the No. 3 cargo door cutout for
cracks, and repair of any crack detected. That AD also provides for
optional structural modification of uncracked frames, which terminates
the repetitive inspections.
Actions Since Existing AD Was Issued
Since we issued AD 86-17-05 R1, we have received reports indicating
that the frame of the No. 3 cargo door cutout was severed on two Model
727-200 series airplanes. Both airplanes had accumulated approximately
24,500 total flight cycles (i.e., approximately 4,800 flight cycles
fewer than the threshold specified in AD 86-17-05 R1 for the initial
inspection of the frame.) We have determined that this damage was a
result of fatigue cracking. Cracking of the forward frame of the No. 3
cargo door cutout, if not corrected, can result in failure of the
forward frame of the No. 3 cargo door cutout and consequent rapid
decompression of the airplane.
Other Relevant Rulemaking
Also since the issuance of AD 86-17-05 R1, we issued AD 90-06-09,
amendment 39-6488 (55 FR 8370, March 7, 1990), for certain Boeing Model
727 series airplanes. That AD requires certain structural modifications
including a frame reinforcement preventative modification of the
forward frame of the No. 3 cargo door cutout. Boeing Alert Service
Bulletin 727-53A0169, Revision 1, dated March 28, 1986; Revision 2,
dated May 23, 1986; Revision 3, dated June 11, 1987; and Revision 4,
dated January 21, 1989; are referenced in Boeing Document D6-54860,
Revision C, dated December 11, 1989 (which is referenced as the
appropriate source of service information for accomplishing the
structural modifications in AD 90-06-09) as acceptable sources of
service information for accomplishing the frame reinforcement
preventative modification of the forward frame of the No. 3 cargo door
cutout. Doing the frame reinforcement preventative modification of the
forward frame of the No. 3 cargo door cutout, as required by paragraph
A. of AD 90-06-09, terminates the repetitive inspections required by
this proposed AD.
Relevant Service Information
We have reviewed Boeing Service Bulletins 727-53A0169, Revision 5,
dated November 2, 1989; and Revision 6, dated September 28, 2002. The
service bulletins describe procedures for an initial penetrant or
visual inspection of the forward and aft sides of the forward frame of
the No. 3 cargo door cutout, including a portion of the exterior skin,
frame web, and inner flanges, to find cracking; and related
investigative and corrective actions, if necessary. The related
investigative actions include performing repetitive inspecting if no
crack is found and following repair of any crack that is found. The
corrective actions include contacting Boeing for repair instructions
for any crack found in the skin and certain cracks found in the frame;
replacing any cracked segment of the frame with a new or serviceable
segment, or repairing any crack found in the frame and reporting
certain information to Boeing following the repair; and inspections for
repairs made previously. The service bulletin also describes procedures
for a frame reinforcement preventative modification of the forward
frame of the No. 3 cargo door cutout that would eliminate the need for
the repetitive inspections. 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
The unsafe condition described previously is likely to exist or
develop on other airplanes of the same type design. We are proposing to
supersede AD 86-17-05 R1. This proposed AD would continue to require
initial and repetitive inspections to find cracking in the forward
frame of the No. 3 cargo door cutout; and corrective actions, if
necessary. This proposed AD would reduce the compliance time for the
initial inspections and add an optional method of inspection for both
the initial and repetitive inspections. This proposed AD would also add
an initial and repetitive inspections of an additional inspection area,
and repair if necessary. Additionally, this proposed AD would clarify
that the previously optional structural modification is now required by
other rulemaking. This proposed AD would also require you to use the
service information described previously to perform these actions,
except as discussed under ``Differences Between the Proposed AD and
Service Information.''
Differences Between the Proposed AD and Service Information
The service bulletin specifies that you may contact the
manufacturer for instructions on how to repair certain conditions, but
this proposed AD would require repairing those conditions in one of the
following ways:
Using a method that we approve; or
Using data that meet the certification basis of the
airplane, and that have been approved by an Authorized Representative
for the Boeing Commercial Airplanes Delegation Option Authorization
Organization whom we have authorized to make those findings.
Boeing Service Bulletin 727-53A0169, Revision 6, dated September
28, 2002, only specifies a ``visual inspection'' (in addition to the
penetrant inspection) for cracking of the forward frame of the No. 3
cargo door cutout. We have determined that the procedures for this
inspection in the service bulletin should be described as a ``detailed
inspection.'' We have included Note 1 in this AD to define this type of
inspection.
Additionally, the service bulletin describes procedures for
accomplishing a structural modification that would terminate the
repetitive inspections also described in that service bulletin. The
service bulletin recommends accomplishing the structural modification
prior to an airplane accumulating 60,000 total flight cycles. We have
determined that this proposed AD should not contain a requirement for
that terminating structural modification, because we have previously
issued AD 90-06-09, which currently requires that structural
modification for the affected airplanes.
Although the Accomplishment Instructions of the service bulletin
describe procedures for submitting inspection findings to Boeing, we
are not requiring that action in this proposed AD.
Clarification of Items Referenced in the Service Bulletin
Paragraph 3.B.7.c. of the Accomplishment Instructions and Step 1 of
Figure 2 of Boeing Service Bulletin 727-53A0169, Revision 6, dated
September 28, 2002, refer to ``Detail 1'' and ``Detail 2.'' However, in
the drawing portion of Figure 2, those details are labeled ``Detail A''
and Detail ``B.'' Therefore, when instructed to refer to Detail 1 of
Figure 2, operators should refer to Detail A; when instructed to refer
to Detail 2 of Figure 2, operators should refer to Detail B. We have
learned that Boeing intends to publish an information notice to inform
operators of this issue.
[[Page 11347]]
Changes to Existing AD
This proposed AD would retain the requirements of AD 86-17-05 R1
(including the requirements of AD 86-17-05). Since AD 86-17-05 R1 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 in
Requirement in AD 86-17-05 R1 this proposed AD
------------------------------------------------------------------------
Paragraph A............................... Paragraph (f).
Paragraph B............................... Paragraph (g).
Paragraph C............................... Paragraph (h).
Paragraph D............................... Paragraph (n).
------------------------------------------------------------------------
We have removed all references to ``later FAA-approved revisions of
the applicable service bulletin'' in the ``Requirements of AD 86-17-05
R1 With Reduced Threshold and New Optional Inspection Method,'' to be
consistent with FAA policy. We cannot use the phrase, ``or later FAA-
approved revisions,'' in ADs because it violates Office of the Federal
Register regulations for approving materials that are incorporated by
reference. However, in paragraph (m) of this proposed AD, we are giving
operators credit for actions done before the effective date of this AD
in accordance with Revision 2, dated May 23, 1986; Revision 3, dated
June 11, 1987; Revision 4, dated January 21, 1988; and Revision 5,
dated November 2, 1989, of Boeing Service Bulletin 727-53A0169. We may
decide to approve later revisions of the service bulletin as an
alternative method of compliance with this proposed AD, as provided by
paragraph (p) of this proposed AD.
We have also changed the term ``landings'' in the ``Requirements of
AD 86-17-05 R1 With Reduced Threshold and New Optional Inspection
Method,'' to ``flight cycles'' to be consistent with the new
requirements of this proposed AD. This change has no effect on the
compliance times specified in the ``Requirements of AD 86-17-05 R1 With
Reduced Threshold and New Optional Inspection Method.''
Costs of Compliance
There are about 269 airplanes of the affected design in the
worldwide fleet. The new requirements of this AD add no additional
economic burden. The current costs for U.S. operators to comply with
this proposed AD are repeated for the convenience of affected
operators, as follows:
Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Number of
Average U.S.-
Action Work hours labor rate Parts cost Cost per airplane registered Fleet cost
per hour airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
Inspections (required by AD 86-17-05 6 $65 None................... $390, per inspection 166 $64,740, per inspection
R1), per inspection cycle. cycle. 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.
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.
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 39-5714 (52 FR
32534, August 28, 1987) and adding the following new airworthiness
directive (AD):
Boeing: Docket No. FAA-2006-24073; Directorate Identifier 2002-NM-
272-AD.
Comments Due Date
(a) The Federal Aviation Administration must receive comments on
this AD action by April 21, 2006.
Affected ADs
(b) This AD supersedes AD 86-17-05 R1.
Applicability
(c) This AD applies to Boeing Model 727-200 series airplanes,
certificated in any category, equipped with a No. 3 cargo door, as
identified in Boeing Service Bulletin 727-53A0169, Revision 2, dated
May 23, 1986.
Unsafe Condition
(d) This AD results from additional reports of cracking in the
forward frame of the No. 3 cargo door cutout. We are issuing this AD
[[Page 11348]]
to detect and correct cracking of the forward frame and fuselage
skin of the No. 3 cargo door cutout, which could result in failure
of the frame and consequent 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.
Requirements of AD 86-17-05 RL With Reduced Threshold and New Optional
Inspection Method
Inspections
(f) At the earlier of the times specified in paragraphs (f)(1)
and (f)(2) of this AD: Do a penetrant or detailed inspection of the
forward frame of the No. 3 cargo door cutout for cracking, in
accordance with paragraph C. of the Accomplishment Instructions of
Boeing Service Bulletin 727-53A0169, Revision 2, dated May 23, 1986.
After the effective date of this AD, the penetrant or detailed
inspection must be done in accordance with paragraph 3.B.3. of the
Accomplishment Instructions of Boeing Service Bulletin 727-53A0169,
Revision 6, dated September 28, 2002. If any cracking is found,
repair in accordance with paragraph (h) or (l) of this AD, as
applicable. Repeat the inspection at intervals not to exceed 2,200
flight cycles, until the preventative modification specified in
paragraph (n) of this AD is done.
(1) Within the next 300 flight cycles after September 3, 1987
(the effective date of AD 86-17-05 R1), or prior to accumulating
29,000 total flight cycles, whichever occurs later, unless
accomplished within the last 1,900 flight cycles.
(2) Prior to accumulating 18,000 total flight cycles, or within
2,200 flight cycles after the effective date of this AD, whichever
occurs later.
(g) At the earlier of the times specified in paragraphs (g)(1)
and (g)(2) of this AD: Do a detailed inspection of the forward frame
of the No. 3 cargo door cutout for cracking, in accordance with
paragraphs D. and E. of the Accomplishment Instructions of Boeing
Service Bulletin 727-53A0169, Revision 2, dated May 23, 1986. After
the effective date of this AD, the detailed inspection must be done
in accordance with paragraphs 3.B.4. and 3.B.5. of the
Accomplishment Instructions of Boeing Service Bulletin 727-53A0169,
Revision 6, dated September 28, 2002. If any cracking is found,
repair in accordance with paragraph (h) or (l) of this AD, as
applicable. Repeat the inspection at intervals not to exceed 2,200
flight cycles, until the preventative modification specified in
paragraph (n) of this AD is done.
(1) Within the next 300 flight cycles after September 3, 1987,
or prior to accumulating 35,000 total flight cycles, whichever
occurs later, unless accomplished within the last 1,900 flight
cycles.
(2) Prior to accumulating 18,000 total flight cycles, or within
2,200 flight cycles after the effective date of this AD, whichever
occurs later.
Repair
(h) Before further flight, repair any crack in the forward frame
of the No. 3 cargo door cutout found before the effective date of
this AD during any inspection required by paragraph (f) or (g) of
this AD, in accordance with paragraph G. of the Accomplishment
Instructions in Boeing Service Bulletin 727-53A0169, Revision 2,
dated May 23, 1986. Repeat the inspections specified in paragraphs
(f) and (g) of this AD at intervals not to exceed 2,200 flight
cycles, for all areas of the forward frame not covered by the
repair, in accordance with the Accomplishment Instructions of
paragraphs C., D., and E. of Boeing Service Bulletin 727-53A0169,
Revision 2, dated May 23, 1986.
New Requirements of This AD
Inspection of Repairs of the Frame Done Before the Effective Date
of the AD
(i) For any repair to the forward frame of the No. 3 cargo door
cutout done, as required by paragraph (h) of this AD, before the
effective date of this AD: Within 18,000 flight cycles following the
repair, or 2,200 flight cycles after the effective date of this AD,
whichever occurs later, do a detailed inspection of the repair for
cracking in accordance with the Accomplishment Instructions of
Boeing Service Bulletin 727-53A0169, Revision 6, dated September 28,
2002. Thereafter, repeat the inspection at intervals not to exceed
2,200 flight cycles, until the preventative modification specified
in paragraph (n) of this AD is done.
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.''
New Inspections of Skin Surrounding the Frame
(j) Prior to the accumulation of 18,000 total flight cycles, or
within 2,200 flight cycles after the effective date of this AD,
whichever occurs later: Do a penetrant or detailed inspection for
cracking of the fuselage skin of the No. 3 cargo door cutout between
stringers S-24 and S-27, in accordance with paragraph 3.B.3. of the
Accomplishment Instructions of Boeing Service Bulletin 727-53A0169,
Revision 6, dated September 28, 2002. Repeat the inspection at
intervals not to exceed 2,200 flight cycles, until the preventative
modification specified in paragraph (n) of this AD is done.
Repair of Cracked Skin
(k) If any crack is found in the fuselage skin during any
inspection required by paragraph (j) of this AD: Before further
flight, repair the crack using a method approved in accordance with
the procedures specified in paragraph (p) of this AD.
Repair of Cracked Frames and Post-Repair Inspections
(l) If, after the effective date of this AD, any crack is found
in the forward frame of the No. 3 cargo door cutout during any
inspection required by paragraph (f), (g), or (i) of this AD: Before
further flight, do the actions specified in paragraph (l)(1),
(l)(2), or (l)(3) of this AD, as applicable. Inspect the repair
within 18,000 flight cycles following the repair, in accordance with
paragraphs 3.B.4. and 3.B.5. of the Accomplishment Instructions of
Boeing Service Bulletin 727-53A0169, Revision 6, dated September 28,
2002. Thereafter, repeat the inspections at intervals not to exceed
2,200 flight cycles, until the preventative modification specified
in paragraph (n) of this AD is done.
(1) If cracks have not severed the inner flange, do an interim
repair using a method approved in accordance with the procedures
specified in paragraph (p) of this AD.
(2) Repair the crack in accordance with paragraph 3.B.7.b. of
the Accomplishment Instructions of Boeing Service Bulletin 727-
53A0169, Revision 6, dated September 28, 2002.
(3) Replace the cracked segment of the frame with a new or
serviceable component and install the frame reinforcement
preventative modification, in accordance with paragraph 3.B.7.c. of
the Accomplishment Instructions of Boeing Service Bulletin 727-
53A0169, Revision 6, dated September 28, 2002. This action
terminates the requirements of this AD.
Repairs Done According to Previous Issues of the Service Bulletin
(m) Inspections and repairs done before the effective date of
this AD in accordance with Boeing Service Bulletin 727-53A0169,
Revision 2, dated May 23, 1986; Revision 3, dated June 11, 1987;
Revision 4, dated January 21, 1988; and Revision 5, dated November
2, 1989, are acceptable for compliance with the corresponding
requirements of paragraphs (h), (k), and (l) of this AD, as
applicable.
Terminating Modification Required by AD 90-06-09
(n) At the same time as the applicable inspections provided in
paragraphs (f), (g), (i), and (j) of this AD are accomplished, doing
the frame reinforcement preventative modification required by
paragraph A. of AD 90-06-09 or the frame reinforcement preventative
modification specified in Figure 2 of Boeing Service Bulletins 727-
53A0169, Revision 5, dated November 2, 1989; and Revision 6, dated
September 28, 2002; terminates the requirements of this AD.
Paragraph A. of AD 90-06-09 references Boeing Document D6-54860,
Revision C, dated December 11, 1989, ``Aging Airplane Structural
Modification Program--Model 727'' as the appropriate source of
service information for accomplishing the frame reinforcement
preventative modification (along with numerous other structural
modifications required by paragraph A. of AD 90-06-09).
Information Submission
(o) Although the service bulletins referenced in this AD specify
to submit
[[Page 11349]]
certain information to the manufacturer, this AD does not include
that requirement.
Alternative Methods of Compliance (AMOCs)
(p) (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) Before using any AMOC approved in accordance with Sec.
39.19 on any airplane to which the AMOC applies, notify the
appropriate principal inspector in the FAA Flight Standards
Certificate Holding District Office.
(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) An AMOC approved previously in accordance with AD 86-17-05
R1, is approved as an AMOC with the corresponding requirements and
provisions of this AD.
Issued in Renton, Washington, on February 23, 2006.
Michael J. Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E6-3221 Filed 3-6-06; 8:45 am]
BILLING CODE 4910-13-P
