[Federal Register: June 30, 2003 (Volume 68, Number 125)]
[Rules and Regulations]
[Page 38583-38586]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr30jn03-1]
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Rules and Regulations
Federal Register
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[[Page 38583]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2003-NM-101-AD; Amendment 39-13209; AD 2003-13-09]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 747 Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; request for comments.
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SUMMARY: This amendment adopts a new airworthiness directive (AD) that
is applicable to certain Boeing Model 747 series airplanes. This action
requires repetitive inspections for cracking of the upper skin of the
outboard and center sections of the horizontal stabilizer and the rear
spar structure, hinge fittings, terminal fittings, and splice plates;
and repair if necessary. This action is necessary to find and fix such
cracking, which could lead to reduced structural capability of the
outboard and center sections of the horizontal stabilizer, and result
in loss of controllability of the airplane. This action is intended to
address the identified unsafe condition.
DATES: Effective July 15, 2003.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of July 15, 2003.
Comments for inclusion in the Rules Docket must be received on or
before August 29, 2003.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 2003-NM-101-AD, 1601 Lind Avenue, SW.,
Renton, Washington 98055-4056. Comments may be inspected at this
location between 9 a.m. and 3 p.m., Monday through Friday, except
Federal holidays. Comments may be submitted via fax to (425) 227-1232.
Comments may also be sent via the Internet using the following address:
9-anm-iarcomment@faa.gov. Comments sent via fax or the Internet must
contain ``Docket No. 2003-NM-101-AD'' in the subject line and need not
be submitted in triplicate. Comments sent via the Internet as attached
electronic files must be formatted in Microsoft Word 97 or 2000 or
ASCII text.
The service information referenced in this AD may be obtained from
Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington
98124-2207. This information may be examined at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at
the Office of the Federal Register, 800 North Capitol Street, NW.,
suite 700, Washington, DC.
FOR FURTHER INFORMATION CONTACT: Tamara Anderson, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
917-6421; fax (425) 917-6590.
SUPPLEMENTARY INFORMATION:
Related AD
This AD is related to AD 2002-06-02, amendment 39-12678 (67 FR
12464, March 19, 2002). Boeing Alert Service Bulletin 747-55A2050,
dated February 28, 2002, was referenced in that AD as the applicable
source of service information for accomplishment of the required
actions. That AD is applicable to all Boeing Model 747 series airplanes
and requires repetitive inspections for cracking of the upper skin of
the horizontal stabilizer center section and the rear spar upper chord,
and repair if necessary. That AD was prompted by a report that a 3.5-
inch crack was found in the upper skin of the horizontal stabilizer
center section on a Boeing Model 747SR series airplane. The actions
specified by that AD are intended to find and fix cracking of the upper
skin of the horizontal stabilizer center section and the rear spar
upper chord, which could lead to reduced structural capability of the
horizontal stabilizer center section, and result in loss of
controllability of the airplane.
Since the Issuance of That AD
The FAA has received 22 reports from two operators of cracking
found on six Model 747 series airplanes with between 20,800 and 37,000
total flight cycles, and between 41,700 and 115,700 total flight hours.
Of the 22 reports of cracking received, the cracking specified in 20 of
the reports was in an area not covered by the Zone A inspections
required by AD 2002-06-02. One operator reported finding two fractured
and three cracked Maraging steel fasteners on an airplane with
approximately 18,700 total flight cycles and 87,300 total flight hours.
Such cracking, if not fixed, could lead to reduced structural
capability of the outboard and center sections of the horizontal
stabilizer, which could result in loss of controllability of the
airplane.
Explanation of Relevant Service Information
We have reviewed and approved Boeing Alert Service Bulletin 747-
55A2050, Revision 1, dated May 1, 2003, which describes procedures for
repetitive inspections for cracking of the upper skin of the outboard
and center sections of the horizontal stabilizer and the rear spar
structure, hinge fittings, terminal fittings, and splice plates; and
repair if necessary. The areas and inspection types are as follows:
[sbull] Zone A Inspections (inspections required by AD 2002-06-02):
Part 1--Detailed inspections for cracking in the upper skin of the
center section and rear spar upper chord. Part 2--High frequency eddy
current (HFEC) inspections for cracking of the upper skin of the center
section and rear spar upper chord. If no cracking is found, the service
bulletin specifies either repeating the detailed inspection or the
doing the Zone A--Part 2 inspection. If cracking is found, the service
bulletin specifies doing the Zone B--Part 4 inspection and repairing
any cracking. Following that inspection and repair, the service
bulletin specifies either repeating the Zone A--Part 1 detailed
inspection or doing the Zone A--Part 2 HFEC inspection.
[sbull] Zone B Inspections (inspections required by this AD):
Part 3--Nondestructive test (NDT) inspections for Groups 1, 2, and
3 airplanes: Includes an ultrasonic inspection for cracking of the
outboard and center sections, rear spar upper
[[Page 38584]]
chords under the hinge fitting halves, upper skins under the splice
plates, and the rear spar webs behind the terminal fittings; a HFEC
inspection for cracking in the terminal fittings around the fasteners;
a low frequency eddy current inspection for cracking in the splice
plates around the fasteners; a surface HFEC inspection for cracking in
the rear spar upper chords in the radius area above the terminal
fittings and the lower surface of the horizontal flange; and a HFEC
inspection for cracking in the rear spar webs in the exposed area above
the terminal fittings.
Part 4--Alternate open hole NDT inspection for Groups 1, 2, and 3
airplanes; recommended for Groups 4, 5, and 6 airplanes: Includes an
open hole HFEC inspection for cracking of the splice plates, terminal
fittings, hinge fitting halves, rear spar upper chords, rear spar webs,
and upper skins; and a magnetic particle inspection or fluorescent
penetrant inspection of the bolts for damage, if applicable. If no
cracking or no damaged hole is found, the service bulletin specifies
either repeating the Part 3 NDT inspections or doing the Part 4 open
hole NDT inspection, as applicable. If cracking or a damaged hole is
found, the service bulletin specifies repairing the cracking and the
damaged hole and repeating the Part 3 NDT inspections or doing the Part
4 open hole NDT inspection, as applicable.
Accomplishment of the actions specified in the service bulletin is
intended to adequately address the identified unsafe condition.
Explanation of the Requirements of the Rule
Since an unsafe condition has been identified that is likely to
exist or develop on other airplanes of the same type design, this AD is
being issued to find and fix cracking of the upper skin of the outboard
and center sections of the horizontal stabilizer and the rear spar
structure, hinge fittings, terminal fittings, and splice plates. Such
cracking could lead to reduced structural capability of the outboard
and center sections of the horizontal stabilizer, and result in loss of
controllability of the airplane. This AD requires accomplishment of the
Zone B inspections for Groups 1, 2, and 3 airplanes as specified in
Parts 3 and 4 of the service bulletin described previously, except as
discussed in the ``Differences'' section below.
This AD does not supersede AD 2002-06-02; therefore, accomplishment
of that AD is still required. Please note that as stated in the
approval section of Boeing Alert Service Bulletin 747-55A2050, Revision
1, dated May 1, 2003, that bulletin has been approved as an alternative
method of compliance to certain portions of AD 2002-06-02.
Interim Action
At this time the FAA is considering a separate rulemaking action to
supersede this AD to address the procedures for repetitive inspections
of Zone C to find additional cracking, and repair of any cracking
found, as described in the service bulletin. That action would also
mandate repetitive inspections of Zone B for Groups 4, 5, and 6
airplanes. Due to the urgency of the need to inspect the fleet and
repair any cracking found, this AD will address only the sections in
the service bulletin that pertain to inspections and repair of Zone B
for Groups 1, 2, and 3 airplanes.
In addition to superseding this AD, that rulemaking action would
also supersede AD 2002-06-02 to mandate long-term inspections of all
affected zones specified in the referenced service bulletin for all 747
series airplanes. However, the planned compliance time for these
actions is sufficiently long so that prior notice and time for public
comment will be practicable.
Differences Between This AD and the Service Bulletin
The effectivity listing of the service bulletin identifies all
Model 747 series airplanes, line number 1 and on, divided into 6
groups, as being subject to the actions described therein. However,
only Model 747 series airplanes having line numbers 1 through 695
inclusive (Groups 1, 2, and 3 airplanes) are included in the
applicability of this AD, as the required actions apply only to the
Zone B inspections for those airplanes.
The service bulletin recommends accomplishing the initial Zone B
inspections for Groups 1, 2, and 3 airplanes within 90 days (after the
issue date of the service bulletin) for airplanes with 27,000 or more
flight cycles or 117,000 or more flight hours. We have determined,
however, that limiting the inspections to airplanes with 27,000 or more
flight cycles or 117,000 or more flight hours would not address all
affected airplanes, in light of the fact that the unsafe condition is
likely to exist or develop on other Model 747 series airplanes. In
developing an appropriate compliance time for all airplanes that are
affected by this AD, the FAA considered not only the manufacturer's
recommendation, but the degree of urgency associated with addressing
the subject unsafe condition, the average utilization of the affected
fleet, and the time necessary to perform the required inspections. In
light of all of these factors, we find that a compliance time of the
later of the following times is warranted for initiating the required
inspections: (1) Before the accumulation of 27,000 total flight cycles
or 117,000 total flight hours, whichever is first; and (2) within 90
days after the effective date of this AD. We find that this compliance
time represents an appropriate interval of time allowable for affected
airplanes to continue to operate without compromising safety.
The service bulletin specifies that the manufacturer may be
contacted for disposition of certain repair conditions; however, this
AD requires the repair of those conditions to be accomplished per a
method approved by the FAA, or per data meeting the type certification
basis of the airplane approved by a Boeing Company Designated
Engineering Representative who has been authorized by the Manager,
Seattle Aircraft Certification Office, to make such findings.
Changes to 14 CFR part 39/Effect on the AD
On July 10, 2002, the FAA issued a new version of 14 CFR part 39
(67 FR 47997, July 22, 2002), which governs the FAA's airworthiness
directives system. The regulation now includes material that relates to
altered products, special flight permits, and alternative methods of
compliance. Because we have now included this material in part 39, we
no longer need to include it in each individual AD; however, this AD
identifies the office authorized to approve alternative methods of
compliance.
Determination of Rule's Effective Date
Since a situation exists that requires the immediate adoption of
this regulation, it is found that notice and opportunity for prior
public comment hereon are impracticable, and that good cause exists for
making this amendment effective in less than 30 days.
Comments Invited
Although this action is in the form of a final rule that involves
requirements affecting flight safety and, thus, was not preceded by
notice and an opportunity for public comment, comments are invited on
this rule. Interested persons are invited to comment on this rule by
submitting such written data, views, or arguments as they may desire.
Communications shall identify the Rules Docket number and be submitted
in triplicate to the address specified under the caption ADDRESSES. All
communications received on or before
[[Page 38585]]
the closing date for comments will be considered, and this rule may be
amended in light of the comments received. Factual information that
supports the commenter's ideas and suggestions is extremely helpful in
evaluating the effectiveness of the AD action and determining whether
additional rulemaking action would be needed.
Submit comments using the following format:
[sbull] Organize comments issue-by-issue. For example, discuss a
request to change the compliance time and a request to change the
service bulletin reference as two separate issues.
[sbull] For each issue, state what specific change to the AD is
being requested.
[sbull] Include justification (e.g., reasons or data) for each
request.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the rule that might
suggest a need to modify the rule. All comments submitted will be
available, both before and after the closing date for comments, in the
Rules Docket for examination by interested persons. A report that
summarizes each FAA-public contact concerned with the substance of this
AD will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this rule must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket Number 2003-NM-101-AD.'' The postcard will be date stamped
and returned to the commenter.
Regulatory Impact
The regulations adopted herein 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. Therefore, it
is determined that this final rule does not have federalism
implications under Executive Order 13132.
The FAA has determined that this regulation is an emergency
regulation that must be issued immediately to correct an unsafe
condition in aircraft, and that it is not a ``significant regulatory
action'' under Executive Order 12866. It has been determined further
that this action involves an emergency regulation under DOT Regulatory
Policies and Procedures (44 FR 11034, February 26, 1979). If it is
determined that this emergency regulation otherwise would be
significant under DOT Regulatory Policies and Procedures, a final
regulatory evaluation will be prepared and placed in the Rules Docket.
A copy of it, if filed, may be obtained from the Rules Docket at the
location provided under the caption ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration 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. Section 39.13 is amended by adding the following new airworthiness
directive:
2003-13-09 Boeing: Amendment 39-13209. Docket 2003-NM-101-AD.
Applicability: Model 747 series airplanes, line numbers 1
through 695 inclusive; certificated in any category.
Compliance: Required as indicated, unless accomplished
previously.
To find and fix cracking of the upper skin of the outboard and
center sections of the horizontal stabilizer and the rear spar
structure, hinge fittings, terminal fittings, and splice plates,
which could lead to reduced structural capability of the outboard
and center sections of the horizontal stabilizer, and result in loss
of controllability of the airplane; accomplish the following:
Repetitive Inspections
(a) At the time specified in paragraph (b) of this AD, do the
Zone B inspections for Groups 1, 2, and 3 airplanes, as required by
either paragraph (a)(1) or (a)(2) of this AD, per the Work
Instructions of Boeing Alert Service Bulletin 747-55A2050, Revision
1, dated May 1, 2003. Repeat the applicable inspection at the
applicable time specified in Sheet 2 of Figure 1 of the service
bulletin.
(1) Do nondestructive test (NDT) inspections for cracking of the
upper skin of the outboard and center sections of the horizontal
stabilizer and the rear spar structure, hinge fittings, terminal
fittings, and splice plates, per Part 3 of the service bulletin. The
inspections include an ultrasonic inspection of the outboard and
center sections, rear spar upper chords under the hinge fitting
halves, upper skins under the splice plates, and the rear spar webs
behind the terminal fittings; a high frequency eddy current (HFEC)
inspection of the terminal fitting around the fasteners; a low
frequency eddy current inspection of the splice plates around the
fasteners; a surface HFEC inspection of the rear spar upper chords
in the radius area above the terminal fitting and the lower surface
of the horizontal flange; and an HFEC inspection of the rear spar
webs in the exposed area above the terminal fitting.
(2) In lieu of the inspections required by paragraph (a)(1) of
this AD: Do an alternate open hole HFEC inspection for cracking of
the splice plates, terminal fittings, hinge fitting halves, rear
spar upper chords, rear spar webs, and upper skins; and a magnetic
particle inspection or fluorescent penetrant inspection for fracture
or cracking of the bolts, if applicable; per Part 4 of the service
bulletin.
(b) Do the inspections required by paragraph (a) of this AD at
the later of the times specified in paragraphs (b)(1) and (b)(2) of
this AD.
(1) Before the accumulation of 27,000 total flight cycles or
117,000 total flight hours, whichever is first.
(2) Within 90 days after the effective date of this AD.
Repair
(c) If any discrepancy (cracking or damage) is found during any
inspection per paragraph (a) of this AD: Before further flight,
repair per the Work Instructions of Boeing Alert Service Bulletin
747-55A2050, Revision 1, dated May 1, 2003. Where the service
bulletin specifies contacting the manufacturer for a repair method:
Before further flight, repair per a method approved by the Manager,
Seattle Aircraft Certification Office (ACO), FAA; or per data
meeting the type certification basis of the airplane approved by a
Boeing Company Designated Engineering Representative who has been
authorized by the Manager, Seattle ACO, to make such findings. For a
repair method to be approved by the Manager, Seattle ACO, as
required by this paragraph, the Manager's approval letter must
specifically reference this AD.
Alternative Methods of Compliance
(d)(1) In accordance with 14 CFR 39.19, the Manager, Seattle
ACO, is authorized to approve alternative methods of compliance
(AMOC) for this AD.
(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 a
Boeing Company Designated Engineering Representative who has been
authorized by the Manager, Seattle ACO, to make such findings.
Incorporation by Reference
(e) Unless otherwise specified in this AD, the actions shall be
done in accordance with Boeing Alert Service Bulletin 747-55A2050,
Revision 1, dated May 1, 2003. This incorporation by reference was
approved by the Director of the Federal Register in accordance with
5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from
Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington
98124-2207. Copies may be inspected at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the
Office of the Federal Register, 800 North Capitol Street, NW., suite
700, Washington, DC.
[[Page 38586]]
Effective Date
(f) This amendment becomes effective on July 15, 2003.
Issued in Renton, Washington, on June 18, 2003.
Kalene Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 03-15855 Filed 6-27-03; 8:45 am]
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