Airworthiness Directives; Boeing Model 747 Airplanes, 68434-68437 [E6-19805]
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68434
Federal Register / Vol. 71, No. 227 / Monday, November 27, 2006 / Rules and Regulations
March 30, 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.
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by adding the following new
airworthiness directive (AD):
I
2006–24–04 Boeing: Amendment 39–14833.
Docket No. FAA–2006–24814;
Directorate Identifier 2006–NM–093–AD.
Effective Date
(a) This AD becomes effective January 2,
2007.
Affected ADs
(b) None.
Applicability
(c) This AD applies to all Boeing Model
767–200, –300, –300F, and –400ER series
airplanes, certificated in any category.
Unsafe Condition
(d) This AD results from fatigue cracks
found in the forward outer chord and
horizontal inner chord at station (STA)
1809.5. We are issuing this AD to detect and
correct cracking in the bulkhead structure at
STA 1809.5, which could result in failure of
the bulkhead structure for carrying the flight
loads of the horizontal stabilizer, and
consequent loss of controllability 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.
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Repetitive Inspections and Corrective
Actions
(f) Before the accumulation of 15,000 total
flight cycles, or within 3,000 flight cycles
after the effective date of this AD, whichever
is later: Do the detailed and high frequency
eddy current (HFEC) inspections for cracking
as specified in Parts 1, 2, 3, and 4 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 767–53A0131, dated
March 30, 2006; and do all corrective actions
before further flight; by accomplishing all the
actions specified in the Accomplishment
Instructions of Boeing Alert Service Bulletin
767–53A0131, dated March 30, 2006, except
as provided by paragraph (g) of this AD.
Repeat the inspections thereafter at intervals
not to exceed 6,000 flight cycles.
Accomplishing the corrective action for the
inspections specified in Part 1, 2, 3, or 4 of
the service bulletin, as applicable, terminates
the repetitive inspections for that area only.
Exception to Service Bulletin
(g) If any cracking is found in the skin or
in any structure other than the forward outer
chord or horizontal inner chord, during any
inspection required by this AD, and Boeing
Alert Service Bulletin 767–53A0131, dated
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Optional Terminating Action
(h) If no cracking is found during the most
recent detailed and HFEC inspections for a
specified area as required by paragraph (f) of
this AD: Modification of a specified area
according to a method approved by the
Manager, Seattle Aircraft Certification Office
(ACO), FAA, terminates the repetitive
inspections required by paragraph (f) of this
AD for that area only. For a forward outer
chord, one approved method is
accomplishment of the actions in Steps 4.A
through 4.C and 4.G through 4.P of Repair 9,
dated April 15, 2006, of Chapter 53–80–08 of
the Boeing 767–200 Structural Repair Manual
(SRM), Document D634T201; Boeing 767–
300 SRM, Document D634T210; Boeing 767–
300F SRM, Document D634T215; or Boeing
767–400 SRM, Document D634T225; as
applicable. For a horizontal inner chord, one
approved method is accomplishment of the
actions in Steps 4.A, 4.B, and 4.F through 4.P
of Repair 10, dated April 15, 2006, of Chapter
53–80–08 of the Boeing 767–200 SRM,
Document D634T201; Boeing 767–300 SRM,
Document D634T210; Boeing 767–300F SRM,
Document D634T215; or Boeing 767–400
SRM, Document D634T225; as applicable.
Credit for Previously Accomplished Repairs
(i) Repair of a forward outer chord done
before the effective date of this AD in
accordance with Repair 9, dated April 15,
2006, of Chapter 53–80–08 of the Boeing
767–200 SRM, Document D634T201; Boeing
767–300 SRM, Document D634T210; Boeing
767–300F SRM, Document D634T215; or
Boeing 767–400 SRM, Document D634T225;
as applicable; is acceptable for compliance
with the requirements of paragraph (f) of this
AD for that area only. Repair of a horizontal
inner chord before the effective date of this
AD in accordance with Repair 10, dated
April 15, 2006, of Chapter 53–80–08 of the
Boeing 767–200 SRM, Document D634T201;
Boeing 767–300 SRM, Document D634T210;
Boeing 767–300F SRM, Document D634T215;
or Boeing 767–400 SRM, Document
D634T225; as applicable; is acceptable for
compliance with the requirements of
paragraph (f) of this AD for that area only.
Alternative Methods of Compliance
(AMOCs)
(j)(1) The Manager, Seattle 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.
(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
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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 767–53A0131, dated March 30,
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 https://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 https://
www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html.
Issued in Renton, Washington, on
November 9, 2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. E6–19797 Filed 11–24–06; 8:45 am]
BILLING CODE 4910–13–P
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
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
AGENCY:
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 inservice 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
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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
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 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:
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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 10inch 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 depressurization. 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.
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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 openhole HFEC inspections or, as a shortterm alternative to open-hole HFEC
inspections, external surface lowfrequency 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
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68435
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
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Federal Register / Vol. 71, No. 227 / Monday, November 27, 2006 / Rules and Regulations
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 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 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
https://dms.dot.gov.
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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.
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
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16:30 Nov 24, 2006
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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
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
I
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by adding the following new
airworthiness directive (AD):
I
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.
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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
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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 § 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
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(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 https://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 https://
www.archives.gov/federal_register/code_of_
federal_regulations/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
VerDate Aug<31>2005
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Jkt 211001
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 71
[Docket No. FAA–2006–26111; Airspace
Docket No. 06–AAL–32]
RIN 2120–AA66
Amendment to Jet Route and Colored
Federal Airways; Alaska
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
SUMMARY: This action amends Jet Route
510 (J–510), and Colored Federal
Airways Amber 2 (A–2), Amber 15 (A–
15), and Green 8 (G–8), Alaska.
Specifically, the FAA is re-designating
J–510 as J–512 because of duplication
with a Canadian Jet Route number,
causing problems with the Flight Data
processors during route validation at the
Anchorage Air Route Traffic Control
Center. Additionally, portions of A–2,
and A–15, and G–8 are discontinuous
between fixes, causing flight processing
software problems, and will be redesignated.
Effective Date: 0901 UTC,
January 18, 2007. The Director of the
Federal Register approves this
incorporation by reference action under
1 CFR part 51, subject to the annual
revision of FAA Order 7400.9 and
publication of conforming amendments.
FOR FURTHER INFORMATION CONTACT: Ken
McElroy, Airspace and Rules, Office of
System Operations Airspace and AIM,
Federal Aviation Administration, 800
Independence Avenue, SW.,
Washington, DC 20591; telephone: (202)
267–8783.
SUPPLEMENTARY INFORMATION:
DATES:
Background
Because of limitations in the Oceans
21 Advanced Technologies and Oceanic
Procedures (ATOP) system scheduled
for operation at Anchorage Center,
several route numbers were identified
that were either duplicated in the
National Airspace System or
discontinuous between fixes. This rule
is necessary to smooth the transition to
ATOP at the Anchorage Center.
Alaskan Jet Routes and Colored
Federal airways are published in
paragraph 2004 and 6009 of FAA Order
7400.9P dated September 1, 2006, and
effective September 15, 2006, which is
incorporated by reference in 14 CFR
71.1. The Federal Airways listed in this
document will be published
subsequently in the Order.
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68437
The Rule
This action amends Title 14 Code of
Federal Regulations (14 CFR) part 71 by
re-designating J–510 as J–512 because
the J–510 designation is duplicated by a
Canadian Jet Route and causes problems
with the Flight Data processors during
route validation at Anchorage Air Route
Traffic Control Center. A–2, and A–15
are discontinuous between the Delta
Junction Non-directional Beacon (NDB)
and the Chena NDB, which also causing
flight processing software problems.
They will be re-designated as A–9 and
A–17 respectively. G–8 is discontinuous
between Kachemak NDB and Campell
Lake NDB and will be re-designated as
G–11. The route number change will
coincide with the effective date of this
rulemaking action.
Accordingly, this action merely
involves editorial change in the route
number of the legal description of a
colored Federal airway, and does not
involve a change in the dimensions or
operating requirements of that airway,
notice and public procedure under 5
U.S.C. 553(b) are unnecessary.
The FAA has determined that this
regulation only involves an established
body of technical regulations for which
frequent and routine amendments are
necessary to keep them operationally
current. Therefore, this regulation: (1) Is
not a ‘‘significant regulatory action’’
under Executive Order 12866; (2) is not
a ‘‘significant rule’’ under Department of
Transportation (DOT) Regulatory
Policies and Procedures (44 FR 11034;
February 26, 1979); and (3) does not
warrant preparation of a regulatory
evaluation as the anticipated impact is
so minimal. Since this is a routine
matter that will only affect air traffic
procedures and air navigation, it is
certified that this rule, when
promulgated, will not have a significant
economic impact on a substantial
number of small entities under the
criteria of the Regulatory Flexibility Act.
Environmental Review
The FAA has determined that this
action qualifies for categorical exclusion
under the National Environmental
Policy Act in accordance with FAA
Order 1050.1E, ‘‘Environmental
Impacts: Polices and Procedures.’’ This
airspace action is not expected to cause
any potentially significant
environmental impacts, and no
extraordinary circumstances exist that
warrant preparation of an
environmental assessment.
List of Subjects in 14 CFR Part 71
Airspace, Incorporation by reference,
Navigation (air).
E:\FR\FM\27NOR1.SGM
27NOR1
]]>Agencies
[Federal Register Volume 71, Number 227 (Monday, November 27, 2006)]
[Rules and Regulations]
[Pages 68434-68437]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-19805]
-----------------------------------------------------------------------
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 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 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 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 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
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.
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 https://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 https://www.archives.gov/federal_
register/code_of_federal_regulations/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
