[Federal Register: September 6, 2005 (Volume 70, Number 171)]
[Proposed Rules]
[Page 52945-52947]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr06se05-22]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-22289; Directorate Identifier 2005-NM-101-AD]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 747-100, 747-100B, 747-
200B, 747-200C, 747-200F, 747-400F, 747SR, and 747SP Series Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for certain Boeing Model 747-100, 747-100B, 747-200B, 747-200C, 747-
200F, 747-400F, 747SR, and 747SP series airplanes, without a stretched
upper deck or stretched upper deck modification. This proposed AD would
require detailed and high-frequency eddy current inspections for cracks
at the outboard ends of each affected tension tie and of the
surrounding structure, and related investigative and corrective actions
if necessary. This proposed AD results from a report of a crack in the
tension tie at the body station 820 frame connection, and cracks found
on the Boeing 747SR fatigue-test airplane in both the tension ties and
frames at the tension tie to frame connections at body stations 800,
820, and 840. We are proposing this AD to find and fix cracks in the
tension ties, which could lead to cracks in the skin and body frame and
result in rapid in-flight depressurization of the airplane.
DATES: We must receive comments on this proposed AD by October 21,
2005.
ADDRESSES: Use one of the following addresses to submit comments on
this proposed 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 the service information identified in this
proposed AD.
FOR FURTHER INFORMATION CONTACT: Ivan Li, Aerospace Engineer, Airframe
Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 1601 Lind
Avenue, SW., Renton, Washington 98055-4056; telephone (425) 917-6437;
fax (425) 917-6590.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to submit any relevant written data, views, or
arguments regarding this proposed AD. Include the docket number ``FAA-
2005-22289; Directorate Identifier 2005--NM-101-AD'' at the beginning
of your comments. We specifically invite comments on the overall
regulatory, economic, environmental, and energy aspects of the proposed
AD. We will consider all comments received by the closing date and may
amend the proposed AD in light of those comments.
We will post all comments we receive, without change, to 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 proposed AD. Using the search function of
that web site, anyone can find and read the comments in any of our
dockets, including the name of the individual who sent the comment (or
signed the comment on behalf of an association, business, labor union,
etc.). You may review 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.
Discussion
We have received a report indicating that, during routing
maintenance on a 747-200F series airplane, one operator found a crack
in the tension tie at the body station (STA) 820 frame
[[Page 52946]]
connection. The crack was 0.125 inch long and located at a fastener
hole. The manufacturer then inspected the 747SR fatigue-test airplane
and found similar cracks in both the tension ties and frames at the
tension ties to the frame connection. The cracks were found at STAs
800, 820, and 840 at 40,000 total flight cycles (20,000 operating
cycles, 20,000 test cycles). Cracks in the frames were up to 1.25
inches long, and cracks in the tension ties were up to 0.20 inch long.
Cracks in the tension ties, if not detected and corrected before they
reach critical crack lengths, could lead to cracks in the skin and body
frame and result in rapid in-flight depressurization of the airplane.
Other Relevant Rulemaking
On September 4, 1984, we issued AD 84-19-01, amendment 39-4913 (49
FR 35365, September 17, 1984) for Boeing Model 747 series airplanes.
That AD was prompted by a report of a crack that occurred during
fatigue testing. That AD requires repetitive close visual inspections
for cracks of the tension tie at STA 760 for certain airplanes and at
STA 780 for certain other airplanes, and repair if necessary. We issued
that AD to detect cracks and prevent failure of the frame to tension
tie joint structure. The airplanes in the applicability of AD 84-19-01
would also be subject to the requirements of this proposed AD.
On June 14, 1994, we issued AD 94-13-06, amendment 39-8946 (59 FR
32879, June 27, 1994), for certain Boeing Model 747 series airplanes.
That AD requires inspections to detect cracking in certain fuselage
upper deck tension ties, and repair or modification of any cracked
tension ties. We issued that AD to prevent failure of two or more
tension ties and the resultant rapid decompression of the airplane. The
airplanes in the applicability of AD 94-13-06 would also be subject to
the requirements of this proposed AD.
On March 24, 2004, we issued AD 2004-07-22, amendment 39-13566 (69
FR 18250, April 7, 2004), for all Boeing Model 747 series airplanes.
That AD requires revising the FAA-approved maintenance or inspection
program to include repetitive inspections for discrepancies of various
structural significant items (SSIs); as listed in Boeing Document No.
D6-35022, ``Supplemental Structural Inspection Document (SSID),''
Revision G, dated December 2000 (referred to after this as ``the
SSID''); and repair if necessary.
Relevant Service Information
We have reviewed Boeing Special Attention Service Bulletin 747-53-
2502, dated April 21, 2005. The service bulletin describes procedures
for doing repetitive detailed and high-frequency eddy current (HFEC)
inspections for cracks at the outboard ends of each affected tension
tie and of the surrounding structure. If any cracking is found, the
service bulletin describes procedures for related investigative and
corrective actions. These actions include doing all applicable repairs
and doing further HFEC inspections of certain fastener holes until the
inspection indicates that the repair has removed all cracking. If the
cracking exceeds certain limits defined in the service bulletin, or if
the area cannot be repaired without exceeding certain limits, or if the
discrepancy is at certain locations defined in the service bulletin,
the corrective action is contacting Boeing for repair instructions.
FAA's Determination and Requirements of the Proposed AD
We have evaluated all pertinent information and identified an
unsafe condition that is likely to exist or develop on other airplanes
of this same type design. For this reason, we are proposing this AD,
which would require accomplishing the actions specified in the service
information described previously, except as discussed under
``Difference Between the Proposed AD and the Service Bulletin.''
Certain actions in this proposed AD are alternative methods of
compliance (AMOCs) for certain actions in the ADs referenced below. All
provisions of the referenced ADs, including applicable post-
modification inspection thresholds, remain fully applicable and must be
complied with.
Repairs of the aft tension tie channels in accordance with
this proposed AD would be AMOCs to the repair requirements of paragraph
A. of AD 84-19-01, and paragraphs (a)(2) and (b)(2) of AD 94-13-06.
The inspection requirements of this proposed AD would be
AMOCs for the post-modification inspection requirements of paragraph B.
of AD 84-19-01, and paragraph (b) of AD 94-13-06.
The inspection requirements of this proposed AD would be
AMOCs for the corresponding requirements of paragraphs (c) and (d) of
AD 2004-07-22 for the inspections of SSI item F-19A of the SSID in the
area addressed by this proposed AD.
Difference Between the Proposed AD and the Service Bulletin
The service bulletin specifies that you may contact the
manufacturer for instructions on how to repair certain conditions, but
this proposed AD would require 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 Commercial Airplanes Delegation Option Authorization
Organization whom we have authorized to make those findings.
This difference has been coordinated with the manufacturer.
Interim Action
We consider this proposed AD interim action. The manufacturer is
currently developing a modification that will address the unsafe
condition identified in this AD. Once this modification is developed,
approved, and available, we may consider additional rulemaking.
Costs of Compliance
There are about 458 airplanes of the affected design in the
worldwide fleet. This proposed AD would affect about 141 airplanes of
U.S. registry. The proposed inspections would take about 8 work hours
per airplane, per tension tie location. There are between 8 and 12
tension tie locations on each airplane, depending on the airplane's
configuration. The average labor rate is $65 per work hour. Based on
these figures, the estimated cost of the proposed AD for U.S. operators
is between $586,560 and $879,840, or between $4,160 and $6,240 per
airplane, per inspection cycle.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
subtitle VII, part A, subpart III, section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
[[Page 52947]]
Regulatory Findings
We have determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify that the proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979); and
3. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to
comply with this proposed AD 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, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. The Federal Aviation Administration (FAA) amends Sec. 39.13 by
adding the following new airworthiness directive (AD):
Boeing: Docket No. FAA-2005-22289; Directorate Identifier 2005-NM-
101-AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by October
21, 2005.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Boeing Model 747-100, 747-100B, 747-200B,
747-200C, 747-200F, 747-400F, 747SR, and 747SP series airplanes,
certificated in any category; without a stretched upper deck or
stretched upper deck modification; as identified in Boeing Special
Attention Service Bulletin 747-53-2502, dated April 21, 2005.
Unsafe Condition
(d) This AD results from a report of a crack in the tension tie
at the body station 820 frame connection, and cracks found on the
Boeing 747SR fatigue-test airplane in both the tension ties and
frames at the tension tie to frame connections at body stations 800,
820, and 840. We are issuing this AD to find and fix cracks in the
tension ties, which could lead to cracks in the skin and body frame
and result in rapid in-flight depressurization 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 and Corrective Actions
(f) At the applicable time in paragraph (f)(1) or (f)(2) of this
AD: Do detailed and high-frequency eddy current inspections for
cracks at the outboard ends of each affected tension tie and of the
surrounding structure. If any cracking is found: Before further
flight, do all applicable corrective and related investigative
actions. Do all actions in accordance with the Accomplishment
Instructions of Boeing Special Attention Service Bulletin 747-53-
2502, dated April 21, 2005. Where the service bulletin specifies to
contact Boeing for repair instructions: Before further flight,
repair the area using a method approved in accordance with paragraph
(g) of this AD.
(1) For airplanes identified in the service bulletin as Group 1,
3, and 6 airplanes: Do the first inspections before the accumulation
of 20,000 total flight cycles, or within 1,000 flight cycles after
the effective date of this AD, whichever occurs later; and repeat
the inspections thereafter at intervals not to exceed 4,000 flight
cycles.
(2) For airplanes identified in the service bulletin as Group 2,
4, and 5 airplanes: Do the first inspections before the accumulation
of 17,000 total flight cycles, or within 1,000 flight cycles after
the effective date of this AD, whichever occurs later; and repeat
the inspections thereafter at intervals not to exceed 3,000 flight
cycles.
Alternative Methods of Compliance (AMOCs)
(g)(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) 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.
(3) Certain actions required by paragraph (f) of this AD are
AMOCs for certain requirements in the ADs identified in paragraphs
(g)(1)(i), (g)(2)(ii), and (g)(3)(iii) of this AD. All provisions of
the referenced ADs, including applicable post-modification
inspection thresholds, remain fully applicable and must be complied
with.
(i) Repairs of the aft tension tie channels done in accordance
with this AD are AMOCs for the repair requirements of paragraph A.
of AD 84-19-01, amendment 39-4913, and paragraphs (a)(2) and (b)(2)
of AD 94-13-06, amendment 39-8946.
(ii) The inspection requirements of this AD are AMOCs for the
post modification inspection requirements of paragraph B. of AD 84-
19-01, and paragraph (b) of AD 94-13-06.
(iii) The inspection requirements of this AD are AMOCs for the
inspections of structural significant item (SSI) F-19A of Boeing
Supplemental Structural Inspection Document D6-35022, Revision G,
dated December 2000, as required by paragraphs (c) and (d) of AD
2004-07-22, amendment 39-13566.
Issued in Renton, Washington, on August 29, 2005.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-17609 Filed 9-2-05; 8:45 am]
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