[Federal Register: June 20, 2006 (Volume 71, Number 118)]
[Rules and Regulations]
[Page 35385-35387]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr20jn06-6]
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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;
Amendment 39-14653; AD 2006-13-01]
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: Final rule.
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SUMMARY: The FAA is superseding an existing airworthiness directive
(AD), which applies to certain Boeing Model 727-200 series airplanes.
That 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 new AD reduces the compliance time for the initial
inspections and adds an optional method of inspection for both the
initial and repetitive inspections. This AD also adds initial and
repetitive inspections of an additional area, and repair if necessary.
Additionally, this AD clarifies that the previously optional structural
modification is now required by other rulemaking. This AD results from
additional reports of cracking in the forward frame of the No. 3 cargo
door cutout. We are issuing 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: This AD becomes effective July 25, 2006.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of July 25, 2006.
ADDRESSES: You may examine the AD docket on the Internet at http://dms.dot.gov
or in person at the Docket Management Facility, U.S.
Department of Transportation, 400 Seventh Street SW., Nassif Building,
Room PL-401, Washington, DC.
Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle,
Washington 98124-2207, for service information identified in this 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:
Examining the Docket
You may examine the airworthiness directive (AD) docket on the
Internet at http://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 street address stated in the ADDRESSES section.
Discussion
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to include an AD that supersedes AD 86-17-05 R1, amendment
39-5714 (52 FR 32534, August 28, 1987). The existing AD applies to
certain Boeing Model 727-200 series airplanes. That NPRM was published
in the Federal Register on March 7, 2006 (71 FR 11345). That NPRM
proposed to continue to require initial and repetitive inspections for
cracks in the forward frame of the No. 3 cargo door cutout; and
corrective actions, if necessary. That NPRM proposed to reduce the
compliance time for the initial inspections and add an optional method
of inspection for both the initial and repetitive inspections. That
NPRM also proposed to add initial and repetitive inspections of an
additional area, and repair if necessary. Additionally, that NPRM
clarified that the previously optional structural modification is now
required by other rulemaking.
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the comments that have been
received on the NPRM.
Request for Clarification of Certain Language
Boeing requests that certain language be added to the Actions Since
Existing AD was Issued section of the NPRM to clarify that the forward
frame is the subject of the findings and that the skin and doubler in
the area are also involved as an area of concern.
We agree that adding the suggested language would clarify the
location of the subject unsafe condition (i.e., the forward frame of
the No. 3 cargo door cutout, along with the surrounding skin and
doubler). However, because that section of the NPRM is not restated in
the final rule, we find that no change to the AD is necessary in this
regard.
Request To Correct AD Number in Restatement of Requirements Heading
Boeing points out that there is a typographical error in the AD
number identified in the ``REQUIREMENTS OF AD 86-17-05 R1 WITH REDUCED
THRESHOLD AND NEW OPTIONAL INSPECTION METHOD:'' heading in the
regulatory text of the NPRM, and requests that the error, ``AD 86-17-05
RL,'' be corrected to read ``AD 86-17-05 R1.''
We agree. We have verified that an error did occur in the AD number
in that heading during printing of the NPRM. That AD number is correct
in this final rule.
Conclusion
We have carefully reviewed the available data, including the
comments that have been received, and determined that air safety and
the public interest require adopting the AD with the change described
previously. We have determined that this change will neither increase
the economic burden on any operator nor increase the scope of the AD.
Costs of Compliance
There are about 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 AD are repeated for the convenience of affected operators, as
follows:
[[Page 35386]]
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Number of
Work Average Cost per U.S.-
Action hours labor rate Parts cost airplane registered Fleet cost
per hour airplanes
----------------------------------------------------------------------------------------------------------------
Inspections (required by AD 6 $65 None......... $390, per 166 $64,740, per
86-17-05 RI), per inspection inspection inspection
cycle. cycle. cycle.
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Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
subtitle VII, part A, subpart III, section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We have determined that this AD will not have federalism
implications under Executive Order 13132. This AD will not have a
substantial direct effect on the States, on the relationship between
the national government and the States, or on the distribution of power
and responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866;
(2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979); and
(3) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to
comply with this AD and placed it in the AD docket. See the ADDRESSES
section for a location to examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The Federal Aviation Administration (FAA) amends Sec. 39.13 by
removing amendment 39-5714 (52 FR 32534, August 28, 1987) and by adding
the following new airworthiness directive (AD):
2006-13-01 Boeing: Amendment 39-14653. Docket No. FAA-2006-24073;
Directorate Identifier 2002-NM-272-AD.
Effective Date
(a) This AD becomes effective July 25, 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 Alert 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
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 R1 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 Alert 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
Alert 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
[[Page 35387]]
Instructions in Boeing Alert 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 Alert 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 Alert Service Bulletin 727-
53A0169, Revision 2, dated May 23, 1986; Boeing Service Bulletin
727-53A0169, 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 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.
Material Incorporated by Reference
(q) You must use Boeing Alert Service Bulletin 727-53A0169,
Revision 2, dated May 23, 1986; or Boeing Service Bulletin 727-
53A0169, Revision 6, dated September 28, 2002; as applicable, to
perform the actions that are required by this AD, unless the AD
specifies otherwise. The Director of the Federal Register approved
the incorporation by reference of these documents in accordance with
5 U.S.C. 552(a) and 1 CFR part 51. Boeing Alert Service Bulletin
727-53A0169, Revision 2, contains the following effective pages:
------------------------------------------------------------------------
Revision
Page number level shown Date shown on page
on page
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1, 3-16......................... 2 May 23, 1986.
2............................... 1 March 28, 1986.
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Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle,
Washington 98124-2207, for a copy of this service information. You
may review copies at the Docket Management Facility, U.S. Department
of Transportation, 400 Seventh Street, SW., Room PL-401, Nassif
Building, Washington, DC; on the Internet at http://dms.dot.gov; or
at the National Archives and Records Administration (NARA). For
information on the availability of this material at the NARA, call
(202) 741-6030, or go to http://www.archives .gov/federal--register
/code--of--federal-- regulations/ibr--locations .html.
Issued in Renton, Washington, on June 9, 2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 06-5498 Filed 6-19-06; 8:45 am]
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