[Federal Register: November 27, 2006 (Volume 71, Number 227)]
[Rules and Regulations]
[Page 68434-68437]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr27no06-3]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-26388; Directorate Identifier 2006-NM-234-AD;
Amendment 39-14834; AD 2006-24-05]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 747 Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain Boeing Model 747 airplanes. This AD requires repetitive
inspections for any cracking of the fuselage skin in section 41 of the
airplane, and related investigative and corrective actions if
necessary. This AD results from a report of fatigue cracks found in the
skin in section 41 of the fuselage, on an in-service Model 747
airplane. We are issuing this AD to detect and correct fatigue cracks
at the fastener rows of the fuselage skin in section 41, which could
[[Page 68435]]
join together and cause a loss of structural integrity and rapid
decompression of the airplane.
DATES: This AD becomes effective December 12, 2006.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in the AD as of December 12,
2006.
We must receive comments on this AD by January 26, 2007.
ADDRESSES: Use one of the following addresses to submit comments on
this AD.
DOT Docket Web site: go to http://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: go to http://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 Boeing Commercial Airplanes, P.O. Box 3707, Seattle,
Washington 98124-2207, for service information identified in this AD.
FOR FURTHER INFORMATION CONTACT: Ivan Li, Aerospace Engineer, Airframe
Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 1601 Lind
Avenue, SW., Renton, Washington 98057-3356; telephone (425) 917-6437;
fax (425) 917-6590.
SUPPLEMENTARY INFORMATION:
Discussion
We have received a report indicating that fatigue cracks were found
in the skin in section 41 of the fuselage, on an in-service Model 747
airplane. A 10-inch skin crack and numerous smaller skin cracks in
multiple adjacent fastener rows were found immediately aft of the left
number 1 main entry door. The cracks occurred less than 7,000 flight
cycles after the terminating action required by AD 2006-20-02,
(described below), had been done. The fatigue cracks are the result of
cyclic loading during cabin pressurization and de-pressurization. Skin
cracks at the fastener rows in section 41 of the fuselage, if not
detected and corrected in a timely manner, could join together and
result in a loss of structural integrity and rapid decompression of the
airplane.
Related AD
On September 14, 2006, we issued AD 2006-20-02, amendment 39-14771
(71 FR 56861, September 28, 2006) (which superseded AD 96-23-02,
amendment 39-9807 (61 FR 57991, November 12, 1996)), for certain Boeing
Model 747 airplanes. That AD requires inspections to detect disbonding,
corrosion, and cracking at the longitudinal rows of fasteners in the
bonded skin panels in section 41 of the fuselage, and repair, if
necessary. That AD also requires inspections of airplanes that may have
Alodine-coated rivets installed. That AD resulted from a report of
cracking discovered in a skin lap joint that was previously inspected
using the eddy current method. We issued that AD to prevent rapid
decompression of the airplane due to disbonding and subsequent cracking
of the skin panels.
Relevant Service Information
We have reviewed Boeing Alert Service Bulletin 747-53A2675, dated
October 12, 2006. The alert service bulletin describes procedures for
repetitive inspections for any cracking of the fuselage skin in section
41 of the airplane, reports of inspection findings to Boeing, and
related investigative and corrective actions if necessary. Repetitive
inspections for any cracking of the fuselage skin includes using
surface high-frequency eddy current (HFEC) inspections or, as a short-
term alternative to surface HFEC inspections, external detailed
inspections of the skin panel around fastener heads; and open-hole HFEC
inspections or, as a short-term alternative to open-hole HFEC
inspections, external surface low-frequency eddy current (LFEC)
inspections of the skin at the edge row fasteners common to an external
doubler and a bonded internal doubler. Related investigative and
corrective actions may involve using a surface HFEC, or an open-hole
HFEC inspection, as applicable, on all the affected fuselage skin in
section 41; and repairing any crack damage as given in the applicable
Boeing 747 Structural Repair Manual, or by contacting Boeing for repair
data.
The alert service bulletin also specifies the following initial
compliance times for the inspections: Within 150 flight cycles after
the date on the alert service bulletin; before the accumulation of
8,000 total flight cycles; or within 2,000 flight cycles after the last
HFEC inspection, Method 1 (external Ultrasonic) or Method 2 (internal
detailed) disbond inspection as given in Boeing Alert Service Bulletin
747-53A2409 (which is referenced in AD 2006-20-02 as the appropriate
source of service information for doing the actions for that AD);
whichever occurs last. The inspections must be repeated at intervals
not to exceed 2,000 flight cycles for the HFEC inspections, and not to
exceed 150 flight cycles for the alternative detailed and LFEC
inspections that are also not to be repeated more than nine times
before the applicable HFEC inspection is started.
FAA's Determination and Requirements of this AD
The unsafe condition described previously is likely to exist or
develop on other airplanes of the same type design. For this reason, we
are issuing this AD to detect and correct fatigue cracks at fastener
rows, which could join together and cause a loss of structural
integrity and rapid decompression of the airplane. This AD requires
accomplishing the actions specified in the service information
described previously, except as discussed under ``Difference Between
the AD and the Alert Service Bulletin.'' The AD also requires sending
the inspection results of each inspection to the manufacturer.
Difference Between the AD and the Alert Service Bulletin
The alert service bulletin specifies that you may contact the
manufacturer for instructions on how to repair certain conditions, but
this AD requires you to repair 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 Delegation Option Authorization Organization who has
been authorized by the FAA to make those findings.
Interim Action
This is considered to be interim action. The manufacturer has
advised that it currently is developing a new inspection program that
will expand the size of the inspection area and add repetitive
inspections that will address the unsafe condition addressed by this AD
and AD 2006-20-02. Once this new inspection program is developed,
approved, and available, we may consider additional rulemaking.
FAA's Determination of the Effective Date
Since an unsafe condition exists that requires the immediate
adoption of this AD, we have found that notice and opportunity for
public comment before
[[Page 68436]]
issuing this AD are impracticable, and that good cause exists to make
this AD effective in less than 30 days.
Comments Invited
This AD is a final rule that involves requirements that affect
flight safety and was not preceded by notice and an opportunity for
public comment; however, we invite you to submit any relevant written
data, views, or arguments regarding this AD. Send your comments to an
address listed in the ADDRESSES section. Include ``Docket No. FAA-2006-
26388; Directorate Identifier 2006-NM-234-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the AD that might
suggest a need to modify it.
We will post all comments we receive, without change, to http://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 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 you may visit
http://dms.dot.gov.
Examining the Docket
You may examine the 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 DOT
street address stated in the ADDRESSES section. Comments will be
available in the AD docket shortly after the Docket Management System
receives them.
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 the 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 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
adding the following new airworthiness directive (AD):
2006-24-05 Boeing: Amendment 39-14834. Docket No. FAA-2006-26388;
Directorate Identifier 2006-NM-234-AD.
Effective Date
(a) This AD becomes effective December 12, 2006.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Boeing Model 747-100, 747-100B, 747-100B
SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 747-
400F, 747SR, and 747SP series airplanes, certificated in any
category; as identified in Boeing Alert Service Bulletin 747-
53A2675, dated October 12, 2006.
Unsafe Condition
(d) This AD results from a report that fatigue cracks were found
in the skin in section 41 of the fuselage, on an in-service Model
747 airplane. We are issuing this AD to detect and correct fatigue
cracks at the fastener rows of the fuselage skin in section 41,
which could join together and cause a loss of structural integrity
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.
Repetitive Inspections, Investigative and Corrective Actions
(f) At the applicable compliance time specified in paragraph
1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2675,
dated October 12, 2006, do the applicable inspection for any
cracking of the fuselage skin in the section 41 area, and do all
applicable related investigative and corrective actions, by
accomplishing all the actions specified in the Accomplishment
Instructions of Boeing Alert Service Bulletin 747-53A2675, dated
October 12, 2006, except as provided by paragraphs (g) and (h) of
this AD. Repeat the applicable inspection at intervals not to exceed
those specified in paragraph 1.E. of the service bulletin. If any
crack is found, do all applicable related investigative and
corrective actions before further flight.
(g) Where Boeing Alert Service Bulletin 747-53A2675, dated
October 12, 2006, recommends an initial inspection threshold
relative to the date on the service bulletin, this AD requires the
initial inspection threshold relative to the effective date of this
AD.
(h) If any crack is found during any inspection required by this
AD, and Boeing Alert Service Bulletin 747-53A2675, dated October 12,
2006, specifies to contact Boeing for appropriate action: Before
further flight, repair the cracking using a method approved in
accordance with the procedures specified in paragraph (j) of this
AD.
Inspection Reports
(i) Submit a report of the findings (both positive and negative)
of the inspections required by paragraph (f) of this AD to Boeing
Commercial Airplanes Group, Attention: Manager, Airline Support,
P.O. Box 3707, Seattle, Washington 98124-2207, at the applicable
time specified in paragraph (i)(1) or (i)(2) of this AD. The report
must include the inspection results, a description of any
discrepancies/crack found, the airplane serial
[[Page 68437]]
number, and the number of landings and flight hours on the airplane.
Under the provisions of the Paperwork Reduction Act (44 U.S.C. 3501
et seq.), the Office of Management and Budget (OMB) has approved the
information collection requirements contained in this AD and has
assigned OMB Control Number 2120-0056.
(1) For each inspection done after the effective date of this
AD: Submit the report within 10 days after the inspection.
(2) For each inspection accomplished prior to the effective date
of this AD: Submit the report within 10 days after the effective
date of this AD.
Alternative Methods of Compliance (AMOCs)
(j)(1) The Manager, Seattle Aircraft Certification Office (ACO),
FAA, has the authority to approve AMOCs for this AD, if requested in
accordance with the procedures found in 14 CFR 39.19.
(2) 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.
Material Incorporated by Reference
(k) You must use Boeing Alert Service Bulletin 747-53A2675,
dated October 12, 2006, 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 this
document in accordance with 5 U.S.C. 552(a) and 1 CFR part 51.
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/[fxsp0]federal--
register/[fxsp0]code--of--[fxsp0]federal--regulations/[fxsp0]ibr--
locations.html.
Issued in Renton, Washington, on November 13, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E6-19805 Filed 11-24-06; 8:45 am]
BILLING CODE 4910-13-P