[Federal Register: November 23, 2007 (Volume 72, Number 225)]
[Rules and Regulations]
[Page 65655-65658]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr23no07-3]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-0194; Directorate Identifier 2007-NM-306-AD;
Amendment 39-15266; AD 2007-23-18]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 747-100B SUD, 747-200B,
747-300, 747-400, and 747-400D Series Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: The FAA is superseding an existing airworthiness directive
(AD) that applies to all Boeing Model 747-100B SUD, 747-300, 747-400,
and 747-400D series airplanes; and Model 747-200B series airplanes
having a stretched upper deck. The existing AD currently requires
repetitively inspecting for cracking or discrepancies of the fasteners
in the tension ties, shear webs, and frames at body stations 1120
through 1220, and performing related investigative and corrective
actions if necessary. This new AD reduces the repetitive interval for
certain inspections. This AD results from new reports of multiple
severed adjacent tension ties, in addition to the previous reports of
cracked and severed tension ties, broken fasteners, and cracks in the
frame, shear web, and shear ties adjacent to tension ties for the upper
deck. We are issuing this AD to detect and correct cracking of the
tension ties, shear webs, and frames of the upper deck, which could
result in rapid decompression and reduced structural integrity of the
airplane.
DATES: This AD becomes effective November 28, 2007.
On April 26, 2006 (71 FR 14367, March 22, 2006), the Director of
the Federal Register approved the
[[Page 65656]]
incorporation by reference of Boeing Alert Service Bulletin 747-
53A2507, dated April 21, 2005.
We must receive any comments on this AD by January 22, 2008.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to http://www.regulations.gov.
Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12140, 1200 New
Jersey Avenue, SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
For service information identified in this AD, contact Boeing
Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-2207.
Examining the AD Docket
You may examine the AD docket on the Internet at http://www.regulations.gov
; or in person at the Docket Management Facility
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this AD, the regulatory evaluation,
any comments received, and other information. The street address for
the Docket Office (telephone 800-647-5527) is in the ADDRESSES section.
Comments will be available in the AD docket shortly after receipt.
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
On March 9, 2006, we issued AD 2006-06-11, amendment 39-14520 (71
FR 14367, March 22, 2006). That AD applies to all Boeing Model 747-100B
SUD, 747-300, 747-400, and 747-400D series airplanes; and Model 747-
200B series airplanes having a stretched upper deck. That AD requires
repetitively inspecting for cracking or discrepancies of the fasteners
in the tension ties, shear webs, and frames at body stations 1120
through 1220, and performing related investigative and corrective
actions if necessary. That AD resulted from reports of severed tension
ties, as well as numerous reports of cracked tension ties, broken
fasteners, and cracks in the frame, shear web, and shear ties adjacent
to tension ties for the upper deck. The actions specified in that AD
are intended to detect and correct cracking of the tension ties, shear
webs, and frames of the upper deck, which could result in rapid
decompression of the airplane.
Actions Since AD Was Issued
Since we issued that AD, two operators reported that, during a
recent inspection of the tension ties, multiple adjacent tension ties
were found severed. One operator reported three adjacent tension ties
severed on a Model 747-300 series airplane with about 18,400 total
flight cycles. The other operator reported two adjacent tension ties
severed on another Model 747-300 series airplane with about 14,000
total flight cycles. Because of the high number of severed adjacent
tension ties on these two airplanes, we have concluded that the
repetitive interval for the Stage 1 inspection (repetitive detailed
inspections for cracking of the tension ties and adjacent structure at
body station (BS) 1120 through BS 1220), as required by AD 2006-06-11,
does not adequately ensure the safety of the fleet. Therefore, we find
it necessary to reduce the repetitive interval of the Stage 1
inspection. The Stage 2 inspection threshold and intervals are
unchanged.
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 supersede AD 2006-06-11. This new AD retains the
requirements of the existing AD, but reduces the repetitive interval
for the Stage 1 inspection. This new AD also requires sending the
inspection results to Boeing.
Difference Between the AD and the Service Bulletin
To address the recent new inspection findings, this AD reduces the
repetitive interval provided in Boeing Alert Service Bulletin 747-
53A2507, dated April 21, 2005 (cited in the existing AD and this
superseding AD as the appropriate source of service information for the
inspections), for the Stage 1 inspection. Boeing concurs with this
change.
Interim Action
Because the extent of cracking in the fleet is not known, the
required inspection reports will help determine the damage condition of
the fleet. Based on the results of these reports, we may determine that
further corrective action is warranted.
FAA's Determination of the Effective Date
An unsafe condition exists that requires the immediate adoption of
this AD; therefore, providing notice and opportunity for public comment
before the AD is issued is impracticable, and good cause exists to make
this AD effective in less than 30 days.
Comments Invited
This AD is a final rule that involves requirements affecting flight
safety, and we did not provide you with notice and an opportunity to
provide your comments before it becomes effective. However, we invite
you to send any written data, views, or arguments about this AD. Send
your comments to an address listed under the ADDRESSES section. Include
``Docket No. FAA-2007-0194; Directorate Identifier 2007-NM-306-AD'' at
the beginning of your comments. We specifically invite comments on the
overall regulatory, economic, environmental, and energy aspects of this
AD. We will consider all comments received by the closing date and may
amend this AD because of those comments.
We will post all comments we receive, without change, to http://www.regulations.gov
, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this AD.
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.
[[Page 65657]]
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 part 39 of the Federal Aviation Regulations (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 39-14520 (71 FR 14367, March 22, 2006) and adding
the following new airworthiness directive (AD):
2007-23-18 Boeing: Docket No. FAA-2007-0194; Directorate Identifier
2007-NM-306-AD; Amendment 39-15266.
Effective Date
(a) This AD becomes effective November 28, 2007.
Affected ADs
(b) This AD affects the following ADs:
(1) This AD supersedes AD 2006-06-11.
(2) As of the effective date of this AD, for the areas inspected
in accordance with this AD, accomplishment of the requirements of
paragraph (f) or (i) of this AD terminates the corresponding
inspection requirements for the upper deck tension ties as required
by paragraphs (c) and (d) of AD 2004-07-22, amendment 39-13566, as
those paragraphs apply to inspections of structural significant item
(SSI) F-19A, as identified in Boeing Document No. D6-35022,
``Supplemental Structural Inspection Document,'' Revision G, dated
December 2000. All other requirements of AD 2004-07-22 continue to
apply.
Applicability
(c) This AD applies to all Boeing Model 747-100B SUD, 747-300,
747-400, and 747-400D series airplanes; and Model 747-200B series
airplanes having a stretched upper deck; certificated in any
category.
Unsafe Condition
(d) This AD results from new reports of multiple severed
adjacent tension ties, in addition to the previous reports of
cracked and severed tension ties, broken fasteners, and cracks in
the frame, shear web, and shear ties adjacent to tension ties for
the upper deck. We are issuing this AD to detect and correct
cracking of the tension ties, shear webs, and frames of the upper
deck, which could result in rapid decompression and reduced
structural integrity 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 Stage 1 Inspections
(f) Do detailed inspections for cracking or discrepancies of the
fasteners in the tension ties, shear webs, and frames at body
stations 1120 through 1220, and related investigative and corrective
actions as applicable, by doing all actions specified in and in
accordance with ``Stage 1 Inspection'' of the Accomplishment
Instructions of Boeing Alert Service Bulletin 747-53A2507, dated
April 21, 2005, except as provided by paragraph (j) of this AD. Do
the Stage 1 inspections at the applicable times specified in
paragraphs (g) and (h) of this AD, except as provided by paragraphs
(f)(1) and (f)(2) of this AD. Any applicable related investigative
and corrective actions must be done before further flight.
(1) Where paragraph 1.E., ``Compliance,'' of the service
bulletin specifies a compliance time relative to the original issue
date of the service bulletin, this AD requires compliance before the
specified compliance time after April 26, 2006 (the effective date
of AD 2006-06-11).
(2) For any airplane that reaches the applicable compliance time
for the initial Stage 2 inspection (as specified in Table 1,
Compliance Recommendations, under paragraph 1.E. of the service
bulletin) before reaching the applicable compliance time for the
initial Stage 1 inspection: Accomplishment of the initial Stage 2
inspection eliminates the need to do the Stage 1 inspections.
Compliance Time for Initial Stage 1 Inspection
(g) Do the initial Stage 1 inspection at the earlier of the
times specified in paragraphs (g)(1) and (g)(2) of this AD.
(1) At the earlier of the times specified in paragraphs
(g)(1)(i) and (g)(1)(ii) of this AD.
(i) At the applicable time specified in paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 747-53A2507, dated
April 21, 2005.
(ii) Before the accumulation of 10,000 total flight cycles, or
within 250 flight cycles after the effective date of this AD,
whichever occurs later.
(2) At the later of the times specified in paragraphs (g)(2)(i)
and (g)(2)(ii) of this AD.
(i) Before the accumulation of 12,000 total flight cycles.
(ii) Within 50 flight cycles or 20 days, whichever occurs first,
after the effective date of this AD.
Compliance Times for Repetitive Stage 1 Inspections
(h) Repeat the Stage 1 inspection specified in paragraph (f) of
this AD at the time specified in paragraph (h)(1) or (h)(2), as
applicable. Repeat the inspection thereafter at intervals not to
exceed 250 flight cycles, until the initial Stage 2 inspection
required by paragraph (i) of this AD has been done.
(1) For airplanes on which the initial Stage 1 inspection had
not been accomplished as of the effective date of this AD: Do the
next inspection before the accumulation of 10,000 total flight
cycles, or within 250 flight cycles after the initial Stage 1
inspection done in accordance with paragraph (f) of this AD,
whichever occurs later.
(2) For airplanes on which the initial Stage 1 inspection had
been accomplished as of the effective date of this AD: Do the next
inspection at the applicable time specified in paragraph (h)(2)(i)
or (h)(2)(ii) of this AD.
(i) For airplanes that had accumulated fewer than 12,000 total
flight cycles as of the effective date of this AD: Do the next
inspection before the accumulation of 10,000 total flight cycles, or
within 250 flight cycles after the effective date of this AD,
whichever occurs later.
(ii) For airplanes that had accumulated 12,000 total flight
cycles or more as of the effective date of this AD: Do the next
inspection at the later of the times specified in paragraphs
(h)(2)(ii)(A) and (h)(2)(ii)(B) of this AD.
(A) Within 250 flight cycles after accomplishment of the initial
Stage 1 inspection.
(B) Within 50 flight cycles or 20 days, whichever occurs first,
after the effective date of this AD.
Repetitive Stage 2 Inspections
(i) Do detailed and high frequency eddy current inspections for
cracking or discrepancies of the fasteners in the tension ties,
shear webs, and frames at body stations 1120 through 1220, and
related investigative and corrective actions as applicable, by doing
all actions specified in and in accordance with ``Stage 2
Inspection'' of the Accomplishment Instructions of Boeing Alert
Service Bulletin 747-53A2507, dated April
[[Page 65658]]
21, 2005, except as provided by paragraph (j) of this AD. Do the
initial and repetitive Stage 2 inspections at the applicable times
specified in paragraph 1.E., ``Compliance,'' of the service
bulletin. Any applicable related investigative and corrective
actions must be done before further flight. Accomplishment of the
initial Stage 2 inspection ends the repetitive Stage 1 inspections.
Exception to Corrective Action Instructions
(j) If any discrepancy; including but not limited to cracking,
or broken, loose, or missing fasteners; is found during any
inspection required by this AD, and Boeing Alert Service Bulletin
747-53A2507, dated April 21, 2005, specifies to contact Boeing for
appropriate action: Before further flight, repair the discrepancy
using a method approved in accordance with the procedures specified
in paragraph (l) of this AD.
Reporting Requirement
(k) At the applicable time specified in paragraph (k)(1) or
(k)(2) of this AD, submit a report of the findings (both positive
and negative) of each Stage 1 inspection required by this AD to
Boeing Commercial Airplanes; Attention: Manager, Airline Support;
P.O. Box 3707 MC 04-ER; Seattle, Washington 98124-2207; fax (425)
266-5562. The report must include the inspection results, a
description of any discrepancies found, the inspections performed,
the airplane serial number, and the number of total accumulated
flight cycles 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 any inspection done after the effective date of this AD:
Submit the report within 30 days after the inspection.
(2) For any inspection done before the effective date of this
AD: Submit the report within 30 days after the effective date of
this AD.
Alternative Methods of Compliance (AMOCs)
(l)(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) To request a different method of compliance or a different
compliance time for this AD, follow the procedures in 14 CFR 39.19.
Before using any approved AMOC on any airplane to which the AMOC
applies, notify your appropriate principal inspector (PI) in the FAA
Flight Standards District Office (FSDO), or lacking a PI, your local
FSDO.
(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) AMOCs approved previously for repairs for compliance with AD
2006-06-11 are approved as AMOCs for the corresponding provisions of
this AD provided that the repaired areas are inspected at the times
specified in this AD, and the inspections are done in accordance
with this AD.
Material Incorporated by Reference
(m) You must use Boeing Alert Service Bulletin 747-53A2507,
dated April 21, 2005, 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 on April 26, 2006 (71 FR 14367, March 22, 2006). 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 FAA, Transport Airplane Directorate, 1601 Lind Avenue,
SW., Renton, Washington; or at the National Archives and Records
Administration (NARA). For information on the availability of this
material at NARA, call 202-741-6030, or go to http://www.archives.gov/federal-register/cfr/ibr-locations.html
.
Issued in Renton, Washington, on November 15, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 07-5794 Filed 11-21-07; 8:45 am]
BILLING CODE 4910-13-P